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MSC-CF-P-69-n
i: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
CSM
RENDEZVOUS
PROCEDURES
N
G MISSION
FINAL
REVISION A
F m %
23 JUNE 1969
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(ACCESSj^l^UMBER)
(THRU)
rtn^mix
(NASA eft OR TMX OR AD NUMBER)
(CODE)
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(CATEGORY)
MAN NF.n SPACECRAFT CENTER
HOUSTON.TEXAS
_ Sp^ngfiejd^Vr
PREPARED BY:
fEOR^
y
V-
Mission G Proq
Apollo Flight ^
Cure's Develri
Crew Operat/c
Ipm'ent Group
ms
McDonnell Douglas Astronautics Company
TTTK. Mosel
Technical Monitor (MDAC ED)
Orbital Procedures Section
Manned Spacecraft Center
APPROVED BY;
J. C. Callihan
Program Manager
Apollo Flight Crew Operations
McDonnell Douglas Astronautics Company
D. W. Lewis
Technical Manager (MDAC ED)
Flight Procedures Branch
Manned Spacecraft Center
TC 1^
P. C. Kramer
Chief Flight Procedures Branch
Manned Spacecraft Center
Assistant Chief for Crew Integration
Flight Crew Support Division
Manned Spacecraft Center
W. 0, No^h
Chief Flnght Cfrew Support Division
Manned Spacecraft Center
D
. K. Slayton/
/^n:ha irtnan. Crew Procedures Control Board
Manned Spacecraft Center
TABLE OF CONTENTS
PAGE
1.0 PURPOSE - - 1
2.0 INTRODUCTION 2
3.0 DISCUSSION OF MAJOR EVENTS 12
3.1 Undocking and Separation 12
3.2 Descent Orbit Insertion 13
3.3 Powered Descent Initiation 13
3.4- Orbital Navigation 14
3.5 CSM Plane Change 14
3.6 Concentric Sequence Initiation 15
3.7 Constant Delta Height and Plane Change 16
3.8 Terminal Phase Initiation 17
\
3.9 TP I to Station -Keeping 18
4.0 NOMINAL ONBOARD RENDEZVOUS' CHECKLIST 20
5.0 NOMINAL MAJOR PROCEDURES SUMMARY 47
5.1 Summary Timeline . 48
5.2 Summary Checklist 58
- 1 1 - '
PAGE
6.0 NOMINAL DETAILED PROCEDURES 59
6.1 Procedures Ground Rules
6.2 Detailed Procedures 64
6.3 Rendezvous Navigation Summary
with Sun Angles 105
6.4 CSM Attitude Summary 106
7.0 LM RESCUE CASES r= — 108
7.1 Partial DOI ( < 25 EPS) (CSM Active) lOg
7.1.1 Summary _ lOg
7.1.2 Plot and Pads HO
7.1.3 Checklist 111
7.2 Partial DOI {>25 EPS) (CSM Active) H2
7.2.1 Summary H2
7.2.2’ Plot and Pads H3
7.2.3 Checklist H4
7.3 No PDI.J + 12 (LM Active) H5
7.3.1 Summary H5
7.3.2 Plot and Pads Hg
7.3.3 Checklist H 7
-m
PAGE
lA No PDI^ + 12 (LM Active) 118
7.4.1" 'Suminary 118
7.4.2 Plot and Pads 119
7.4.3 Checklist 120
7.5 <1 60 No'PDI^ + 12’(CSM Active) - 121
7.5.1 Summary 121
7.5.2 Plot and Pads 122
7.5.3 Checklist 123
7.6 ^60 No PDI^ + T2 (CSM Active) 124
7.6.1 Summary 124
7.6.2 Plot and Pads 125
7. 6. "3 Checklist 126
7.7 <40 No PDI 2 + 12 (CSH Active) ‘ 127
7.7.1 Summary 127
7.7.2 Plot and Pads 128
7.7.3 ' Checklist 129
7.8 40 - 90 No PDI 2 + 12 {CSM Active) 130
7.8.1 Summary 130
7.8.2 Plot and Pads 131
7.8.3 Checklist 132
-IV-
PAGE
7.9 ^ 90 No PDI 2 + 12 (CSM Active) 133
7.9.1 Summary 133
7.9.2 Plot and Pads — 134
7.9.3 Checklist — 135
7.10 PDI-| < 10 Variable Insertion (LM Active) — 136
7.10.1 Summary 136
7.10.2 Plot and Pads 137
7.10.3 Checklist 138
7.11 PDI^ + 12 (10-12.5 Minutes) (CSM Active) — 139
7.11.1 Summary 1 39
7.11.2 Plot and Pads 140
7.11.3 Checklist — 141
7.12 PDI-, + 14:12 (12.5-15 Minutes) (CSM Active)- 142
7.12.1 Summary -]42
7.12.2 Plot and Pads 143
7.12.3 Checklist ■]44
-V-
PAGE
7.13 PDI. + 21:24 Preferred Lift-off (T^)
' (CSM Active) 145
7.13.1 Summary 145
7.13.2 Plot and Pads 146
7.13.3 Checklist 147
7.14 PDI 2 < 14.5 Variable Insertion (LM Active) - 148
7.14.1 Summary 148
7.14.2 ' Plot and Pads 149
7.14.3 Checklist ■. 150
7.15 PDI^ + 19:22 Preferred Lift-off (Tp)
(CSM Active) 151
7.15,1. Summary 151
7.15.2 Plot and Pads 152
7.15.3 Checklist 153
8.0 REFERENCES
154
-VI-
FIGURES
PAGE
Relative Motion Profile (2-1) 5
LUNAR ORBIT RENDEZVOUS ATTITUDE TIME HISTORY
Undocking - DOI (2-2) — - . 6
PDI (2-3) - 7
P22 Navigation (2-4) 8
CSM Plane Change (2-5) 9
Lift-off - CSI (2-6) 10
CDH - TPF (2-7) 11
vii
LIST OF ACRONYMS AND ABBREVIATIONS
ACQ
ADO
AOH
AOS
ATT
AWY
BEF
B/U
CAL IB
CB -
CDH
CDR
CM
CMC
CMD
CMP
COAS
CSI
CSM
CT
DAP
DH
DOI
DPS
DSKY
DV
DWN
EMS
ET
FDAI
FPS
Acquisition
Adjust
Apollo Operations Handbook
Acquisition of Signal
Attitude
Away
Blunt End Forward
Backup
Calibration
Circuit Breaker
Constant Delta Height
Coirmander
Command Module
Command Module Computer
Command Module Commander's Position
Command Module Pilot
Crew Optical Alignment Sight
Concentric Sequence Initiation
Command and Service Module
Cease Tracking
Digital Autopilot
Delta Height
Descent Orbit Insertion
Descent Propulsion System
Display and Keyboard
Delta Velocity
Down
Entry Monitor System
Event Timer
Flight Director Attitude Indicator
Feet Per Second
-vm-
FWD
Forward
GDC
Gyro Display Coupler
GET
Ground Elapsed Time
GETI
Ground Elapsed Time of Ignition
GMBL
Gimbal
GND
Ground (Mission Control)
GPI
Gimbal Position Indicator
HA
Apogee Altitude
HGA
High-Gain Antenna
HOR
Horizon
HORIZ
Horizontal
HP
Perigee Altitude
IMU
Inertial Measurement Unit
INS
Insertion
IT
Initiate Tracking
I VC
Inter-Vehicular Communication
LEB
Lower Equipment Bay
LGC
LM Guidance Computer
LLMK
Lunar Landmark
LM
Lunar Module
LMK
Landmark
LMP
Lunar Module Pilot
LOI
Lunar Orbit Injection
LOS
Loss of Signal
LV
Launch Vehicle
MNVR
Maneuver
MCC
Midcourse Correction
MCC-H
Mission Control Center - Houston
MDC
Main Display Console
MGA
Middle Gimbal ‘‘Angle
MSFN
Manned Space Flight Network
MTCS
Move to Command Seat
MTLEB
Move to Lower Equipment Bay
MTVC'
Manual Thrust Vector Control
NAV
Navigation
-ix
OPT
Optics
OPDEAL
Orbital Rate Drive Earth and Lunar
OSS
Optical Subsystem
PAD
Data Voiced to Crew From Ground
PB
Pushbutton
PC
Plane Change
PDI
Powered Descent Initiation
PGNCS
Primary Guidance, Navigation, and Control System
PHS
Phasing
PIPA
Pulse Integrating Pendulous Accelerometers
PLM
LM Pitch Angle
PRO
Proceed
PROG
Program
PROP
Propellant
R
Range
RCS
Reaction Control System
ROOT
Range Rate
REFSMMAT
Reference Stable Member Matrix
RHC
Rotation Hand Controller
RR
Rendezvous Radar
S
Shaft
SC
Spacecraft
scs
Stabilization and Control System
SCT
Scanning Telescope
SECS
Sequence Events Control System
SEE
Small End Forward
SEP
Separation
S-IVB
Saturn S-IVB Stage
SM
Service Module
SPS
Service Propulsion System
s/u
Setup
SXT
Sextant
SYNC
Synchronize
TEI
Transearth Injection
TEMCC
Transearth Midcourse Correction
-X-
TFI Time From Ignition
THC Translation Hand Controller
THETA Angle Between SC +X Axis and Local Horizontal
TIGN Time of Ignition
TLI Translunar Injection
TLM Telemetry
TLMCC Translunar Midcourse Correction
TPF Terminal Phase Finalization
TPI Terminal Phase Initiation
TRUN Trunnion
TVC Thrust Vector Control
VG Velocity to be Gained
VHF Very High Frequency
(XX:XX) Indicates GET From Liftoff in Hours :Minutes
(XXX:XX:XX) Indicates GET From Liftoff in Hours :Minutes rSeconds
(XXX,XXX/XXX,XXX) Roll, Pitch ORDEAL/Pitch INERTIAL, Yaw
{XX, XX, XX) Local Vertical DV’s
ANG Antigua Near Space Support Station
BDA Bermuda Near Space Support Station
CRO Carnarvon Near Space Support Station
CYI Canary Near Space Support Station
GYM Guaymas Near Space Support Station
HSK Honeysuckle Deep Space Support Station
HTV Huntsville Near Space Support Station
MAD Madrid Deep Space Support Station
MER Mercury Near Space Support Ship
MIL MILA Near Space Support Station
RED Redstone Near Space Support Ship
TEX Corpus Christi Near Space Support Station
VAN Vanguard Near Space Support Ship
- 1 -
1 .0 PURPOSE
This document contains the nominal GNCS crew procedures
for the CSM-107 spacecraft which will be the target vehicle
for the LM-5 active lunar orbit rendezvous. The procedures
are given in the form of an onboard rendezvous checklist and
as a set of detailed CSM procedures. Also included are onboard
rendezvous checklists for fifteen LM rescue and abort cases.
Detailed Test Objective H, Reference 8.1, subject "Landing LM
Location" will be satisfied during this portion of the mission.
The purpose of the CSM Rendezvous Procedures document is to
provide a single source of procedures information for use in
flight planning, in crew training, and in preparing onboard
data.
This is a control document, subject to review by all elements
of the Apollo Program and to approval by the Procedures
Configuration Control Board. Comments should be directed to
Mr. Duane K. Mosel, Flight Procedures Branch, Flight Crew
Support Division, Extension 5340 or Mr. Richard J. Otto, Jr.,
Apollo Flight Crew Support Group, Houston Operations, McDonnell
Douglas Astronautics Company, Extension 6101.
- 2 -
2.0 INTRODUCTION
The CSM-107/LM-5 lunar orbit rendezvous exercise will begin
during the thirteenth revolution with undocking at 100:15:00 and
end at approximately 127:40-38 with post rendezvous station
keeping. The CSM procedures during this period are divided
into nine segments of major activities which are discussed
in detail in Section 3.0.
A nominal CSM-107/LM-5 mission profile is contained in
Figure (2-1). This figure shows the locations in time and
relative positions in space of the most significant nominal
mission events. Trajectory data used to generate the mission
profile, and timeline for procedures development were obtained
from Reference 8. 18. The rendezvous navigation update schedule
assumed in the procedures was obtained from References 8.3
and 8.5. The schedule indicates tracking periods and assumes
a one mark per minute frequency for both $XT and VHF marks
taken during a track period. The minimum number of marks
required during a tracking period are specified in the
rendezvous checklist. However, it is recommended that more
than the minimum number be planned since systems monitoring
requirements or target visibility problems often pre-empt
taking all the planned marks. In addition, the general
rules for SXT/VHF marking as defined in Reference 8.4 should
be followed.
-3-
A history of the CSM body attitudes during the rendezvous
accompanies the major events discussed and is presented
in Figures (2-2) through (2-7). Each figure illustrates
the body attitudes with respect to the Moon, Sun, and
Earth and indicates FDAI roll, pitch, and yaw gimbal
angles and the ORDEAL pitch angle for significant events
during each lunar orbit. The orbital position of the CSM
at each event is assumed and no attempt is made to show
the LM orbital position other than the indication of it
being above (below) and behind (ahead) the CSM.
Sections 4.0, 5.0, and 6.0 contain the onboard nominal
rendezvous checklist; a summary timeline and summary check-
list for the nominal mission, and the procedures ground
rules, detailed nominal mission procedures, and CSM attitude
summary, respectively. Section 7.0 includes a description
of the 15 abort and rescue cases as described in Reference
8.14. Also the one-page onboard rescue checklist and rela-
tive motion plot and pad page for each of the 15 abort and
rescue cases are included. These cases are:
1) Partial DOI ( < 25 FPS) (CSM Active)
2) Partial DOI ( > 25 FPS.) (CSM Active)
3) No PDI-, +12 (LM Active)
4) No PDI 2 + 12 (LM Active)
5) < 60 No PDI^ + 12 (CSM Active)
6) > 60 No PDI^ + 12 (CSM Active)
7) < 40 No PDl 2 + 12 (CSM Active)
8) 40 - 90 No PDI 2 + 12 (CSM Active)
-4-
9)
10 )
11 )
12 )
13)
14)
15)
^ 90 No PDI 2 + 12 (CSM Active)
PDI^ < 10 Variable Insertion (LM Active)
PDI^ + 12 (10-12.5 Minutes) {CSM Active)
PDI^ + 14:12 (12.5-15 Minutes) (CSM Active)
PDI^ + 21:24 Preferred Lift-off (T^) (OSM Active)
PDIg < 14.5 Variable Insertion (LM Active)
PDI 2 + 19:22 Preferred Lift-off (T 2 ) (CSM Active)
MISSION S - RELATIVE MOTION FOR LM ACTIVE RENDEZVOUS LM CENTERED
FIGURE 2-1
#«£ 5
m SEP TO L« TOUGHDOWH '
mmm to tpf
LIPT*Orr 112 * 23 25> ,
C$H t0.3OO/Z(>S>'»
- 6 -
FIGURE 2-2
MISSION G1 - LUNAR ORBIT RENDEZVOUS
ATTITUDE TIME HISTORY FOR THE CSM
LM DO I
{101 :38:if8)
P20
( 101 :kk)
(0,22 V313,0)
P20
( 102 : 00 )
(0,289/327,0)
-7-
FIGURE 2-3
MISSION G1 - LUNAR ORBIT RENDEZVOUS
ATTITUDE TIME HISTORY FOR THE CSM
- 8 -
Fl GURE 1-h
MISSION 61 - LUNAR ORBIT RENDEZVOUS
ATTITUDE TIME HISTORY FOR THE CSM
MISSION G1 - LUNAR ORBIT RENDEZVOUS
ATTITUDE TIME HISTORY FOR THE CSM
FIGURE 2-5
(107:26)
MNVR TO
SLEEP ATTITUDE
[82,128/218,0)
FIGURE 2-6
MISSION G1 - LUNAR ORBIT RENDEZVOUS
ATTITUDE TIME HISTORY FOR THE CSM
P20
E
- 12 -
3.0 DISCUSSION OF NOMINAL MAJOR EVENTS
3.1 Undocking and Separation
The preparation for undocking includes obtaining a MCC-H
uplink of the CSM vector and copying the separation maneuver
pad at 99:10, Forty-three minutes prior to undocking an
automatic maneuver to the undocking attitude is performed
using extended verb 49. This attitude is identical inertially
to the separation burn attitude except for the 14-degree
yaw which is required during a pre-undocking LM AGS calibra-
tion. Prior to undocking, the CSM is yawed to zero degrees,
a RR transponder check is made, the GDC is aligned to the
IMU, the FDAI ORDEAL is verified, and the DAP is reloaded to
reflect a CSM only configuration. At 100:15 undoekigg is
performed after which the CSM will station keep in SCS control
at about 40 feet. The CMP will then inspect and photograph
the LM landing gear and descent engine bell as the LM does a
360-degree yaw maneuver. Prior to the CSM-active separation
burn at 100:39:58, the^CMP will load -the ExternallDV 'Program,
P30, with a minus 2.5 FPS VG^ {local vertical). The RCS
Thrust Program, P41 , will be called and an automatic maneuver
will be made to the burn attitude which is shown in Figure (2-2).
(This should be a very small maneuver since the undocking at-
titude was the inertial separation burn attitude.) The burn
will be accomplished by thrusting aft in the CSM minus X
direction (i.e., radially down) and increasing the DSKY
(body) from a plus 2.5 FPS to 5 FPS. The HGA can be utilized
for communication during the separation burn.
-13-
3.2 Descent Orbit Insertion
Following the CSM separation burn, the Rendezvous Navigation
Program, P20, will be called and the CSM maneuvered auto-
matically 42 degrees to the preferred track axis for LM radar,
VHF range, and optics checks. At 100:52 the
PDI-| + 12 abort pads, and the CSM rescue pad will be copied.
An IMU realign to REFSMMAT will be performed after sunset at
101':00 using the-TMU Realign Program, P52. At approximateJy
lOlrlO-CSM and' LM state vectors will be uplinked by MCC-H.
Since the CSM does not backup the DOI burn, its only function
will be to monitor the LM burn and hold an attitude which pro-
vides radar transponder coverage. This will be done in Program
P20 with SXT tracking along the preferred track axis. The
Target DV Program, P76, will be loaded with the LM DOI burn
parameters and these data incorporated when the burn is con-
firmed by the LM. LM DOI occurs at 101:38:48.
The attitude of the CSM from the CSM separation burn through
LOS prior to the LM DOI burn is favorable for HGA communications
3.3 Powe red- Descent Initiation
Following the DOI burn, Program P20 will be called and the CSM
attitude will be trimmed to the preferred track axis, if
required. The CMP will confirm that the rendezvous navigation
program is tracking the LM correctly. A period of SXT/VHF
marking is scheduled at 101;52 At! 102:1 7-tbe-W will -cease
tracking and maneuver in order to acquire MSFN with the HGA .
At 102:19 Program P20 will be called and-the.GSM wTTl -be '-j"
- 14 -
maneuvered to the preferred track axis. Four minutes
prior to PDI the CMP will enter Program POO. The DAP
will be loaded with a maneuver rate of .2 degree
per second In order to maintain the LM in the SXT
during powered descent. Extended verb 49 is used
to initiate the pitch down rate at one minute after
PDI initiation. At 102:35:14 the LM powered descent will
be initiated with nominal touchdown occurring at 102:47:11
The CSM has HGA coverage from AOS until the P20 tracking
is initiated. HGA coverage is again acquired during the
LM powered descent,
3.4 Orbital Navigation
Following LM touchdown, a IMU realign to REF5MMAT will be
performed at 103:01, using the IMU Realign Program, P52.
The GDC will be aligned to the IMU and ORDEAL will be
^verified. At 103:47 the orbital navigation PAD will be
copied. At 104:01 a' manual maneuveruto the tracking'^ ^
attitude will be performed. At 104:07 a pitch rate will
be initiated to offset orbital motion during the P22 tracking
sequence. The Orbital Navigation Program, P22, will be
called at 104:07 and the PAD information will be loaded.
The CMP will take five SXT marks on the landing site.
3.5 CSM Plane Change
Following the P22 tracking, the CSM is maneuvered at 104:43
to acquire MSFN. At about 104;'59, MCC-H uplinks the plane
change REFSMMAT. The IMU is aligned to the plane change
REFSMMAT using the gyro torquing technique in the IMU
- 15 -
Realign Program, P52, at 105:04. The GDC is then aligned
to the IMU. At 105:27 the Ground Track Determination
Program, P21 , may be called. At 106:15 the plane change
PAD is recorded and the CSM state vector and target load
are uplinked by MCC-H. At 106:37 the CSM is maneuvered
to the plane change burn attitude. P30 is called at 106:52
and the plane change burn parameters are loaded. The SPS
thrusting program, P40, is entered at 106:56. The CSM
plane change burn occurs at '107:05:34. At 107:08 the
CSM reacquires MSFN and the lift-off REFSMMAT is uplinked
into the CMC, The platform is aligned to the lift-off
REFSMMAT at 107:14 using the same procedure described
above. The CSM is then maneuvered to the rest attitude.
3.6 Concentric Sequence Initiation
Immediately following the insertion burn, a P52 IMU re-
align to REFSMMAT will be performed and the MCC-H will
uplink the LM state vector to the CMC. The LM vector ‘^ill
be that computed by the LM after insertion and relayed to
the ground.
Program P20 will then be called and an automatic trim
maneuver will be made to the preferred track attitude. At
124:48 the CSI Targeting Program, P32, is called and the
CSM backup CSI targeting parameters are loaded. The CSM CSI
burn will be targeted for 125:2,1:20 which is identical to the
LM TIGN. A period of SXT/VHF marking will then take place
from 124:50 to 124:55 followed by a period of VHF only marks
to 125:09, Concurrently with the VHF only tracking, the CMP
will obtain the LM and CSM out-of-plane velocities from
extended verb 90 for inclusion in the LM and CSM CSI targeting
programs .
-16-
Program P40 will be called at 125:13 and an automatic
pitch maneuver of 76 degrees will be made to the backup
CSl burn attitude. At approximately 125:15 the LM will
voice over its CSI solution for P76. The LM CSI burn
occurs at 125:21:20, After verification of the nominal
LM CSI burn, the CMP will incorporate the LM burn para-
meters in Program P76,
The CSM attitude, as specified in Figure (2-6) is compatible
with HGA coverage from insertion through LOS at 125:08.
3.7 Constant Delta Height and Plane Change
At 125:27 approximately five minutes after the LM CSI burn.
Program P20 will be called and an automatic maneuver of 30
degrees will be made to the preferred track axis, A period
of SXT/VHF marks occurs from 125:29 to 125:50. At 125:32
after three SXT/VHF marks, the WR matrix (2000,2) will be
loaded. Extended verb 90 will be called at 125:43 and the
out-of -plane targeting parameters for the LM plane change
maneuver will be computed and voiced to the LM. The CSM
onboard state vectors are used instead of the LM state vectors,
because the CSM knowledge of the out-of -plane positions with
SXT tracking is more accurate than the LM knowledge of
out-of-plane positions with radar tracking. Following the LM
plane change burn at 125:50:40, the target DV parameters are
incorporated into the LM state vector. Since the CSM normally
does not backup the LM plane change burn, a trim maneuver to
the preferred track axis should not be required when Program P20
is called at 125:53. SXT and VHF marks will be taken -
-17-
from 125:53 to 126:05, at which time tracking is terminated
and the CSM will voice to the LM an extended verb 90 out-of -plane
solution. At 126:10 the CDH Targeting Program, P33, will be
called and the CSM backup CDH burn will be targeted for 126:19:40
which is the LM TIGN. The RCS Thrust Program, P41 , is called
at 126:14 and the burn attitude maneuver is bypassed for the
nominally small burn. Approximately four minutes before the
LM CDH burn, the CMP copies the LM CDH pad for later loading of
Program P76. Following the LM CDH burn at 126:19:40, Program
P76 is called and the LM CDH burn incorporated into the CMC LM
state vector.
The CSM attitude, as specified in Figure (2-7), is not compatible
with HGA coverage from AOS until the end of the track period at
about 126:05.
3.8 Terminal Phase Initiation
After completion of the LM CDH burn, Program P20 will be called
which will request an automatic maneuver of 27 degrees to the
preferred tracking attitude. SXT and VHF marks are sbheduled for
a period-starting at 126:24. It is probable that sun interference
in the SXT will limit the total number of SXT marks to 11 taken in
darkness. At 126:30, Program P34 will be called and the CSM backup
TPI burn data will be loaded with the elevation angle option.
After obtaining a CSM TPI TIGN, P34 will be terminated by recalling
P20. SXT and VHF marks are scheduled from 126:34 until 126:45, After
moving to the command seat, the CMP will verify the ORDEAL FDAI. He
will then recall P34, and using the TIGN option with the LM computed
LM TIGN, compute the CSM TPI backup burn parameters. However, if the
LM PGNCS has failed, the CMP will obtain a TPI solution based upon the
elevation angle option. Program P40 will be called and an automatic
^18-
maneuver of 52 degrees will be made to the TPI burn attitude.
The TPI burn will nominally be performed at 126:58:27 with a
CSM to LM' elevation angle of 208.3 degrees. After the LM has
completed the burn, the CMP will incorporate the LM target DV
in Program P76. As seen in Figure (2-7), the CSM has HGA
coverage from prior to CDH through the TPI burn.
3.9 TPI to Station Keeping
After the TPI burn, Program P20 will be called and the CSM
will be automatically maneuvered 34 degrees to the preferred
track attitude. The CMP will move to the LEB during the
maneuver, call the MCC Targeting Program, P35, and take SXT
and VHF marks for eight minutes starting at 127:02. After
obtaining the MCCl solution in Program P35 he will compare it
with -the LM solution and call Program P41 in preparation for the
backup burn. The CSM will not maneuver from the preferred track-
ing attitude. The MCCl burn will nominally be performed by the
LM at 127:13:27 (TPI plus 15 minutes). After MCCl the CMP will
incorporate the LM MCCl Target DV in Program P76.
Following MCCl, Program P35 will be called and an automatic trim
to the preferred tracking attitude will be made if required. SXT
and VHF marks will be taken for a period of nine minutes terminating
at 127:25 The MCC2 solution will be compared with the LM MCC2
solution, after which Program P41 will be called. The CSM will
remain at the preferred tracking attitude while the LM performs
MCC2 at 127:28:27 (TPI plus 30 minutes). After MCC2 the CMP
will incorporate the LM Target DV in Program P76.
-19-
The CSM will then be maneuvered automatically 37 degrees to
the COAS tracking attitude using extended verb 89 while the
CMP moves back to the command seat. The Thrust Monitor Pro-
gram, P47, will be called at a range of 1.25 nautical miles
and VHP ranging data and V83 will be used to monitor the LM
line-of-sight control and braking. Should the LM experience
difficulty, the CSM will perform the line-of-sight control
and braking. The braking gates are specified in the check-
list of Section 4.0. TPF nominally occurs at 127:40:38.
- 20 -
4.0 NOMINAL ONBOARD RENDEZVOUS CHECKLIST
The nominal CSM onboard rendezvous checklist is presented in
this section. The rendezvous checklist was formulated to be
compatible with crew operations in simulators, and in flight.
Therefore, the checklist reflects procedures ,^in an extremely
abbreviated form. The narrative presented in Section 3.0
provides a word description of the checklist events. The
rendezvous checklist procedures have in part been verified
on a man-in-the-loop simulator. Additional simulations
will occur before launch and the rendezvous checklist updated
accordingly to produce a verified checklist.
The nominal onboard rendezvous checklist includes procedures
for performing CSM GNCS activities required during the
LM active rendezvous. Activities required for the opera-
tion and/or monitoring of systems other than the GNCS are
included in the rendezvous checklist by the appropriate systems
personnel .
99 : 30
-23-
6/23
99 : 30 -
L
S ^
V62-SC CONT-CMC-AUTO
-V49; m\IR TO UNDOCKING ATTITUDE (0,244/14,14)
(INERTIAL SEP ATT EXCEPT 14° YAW)
UNDOCK GET 100: ] 5: 00
CONFIGURE CAMERA:
CM/SEQ/18/CEX-BRKT (RH WIN)
MIR (fll,250, oo) 6FPS, 15 MIN
-PREPARE TV CAMERA FOR USE (WINDOW NO. 2)
99 : 40 -
99 : 50 -
lOOSOO-
-CMC MODE-FREE (AS REQ FOR AGS CALIB)
CMC MODE-AUTO (AFTER 32 SEC)
VERIFY MAX DB FOR AGS CALIB
SYSTEMS CHECKS AND SWITCH VERIFICATION
WAIT FOR LM TO COMPUTE AGS ALIGN & GIVE GO, THEN
YAW 14° LEFT AFTER LM AGS CALIB (0,313/14,0)
RR XPNDR CHECKS: (CONFIRM LM RR SELF TEST COMPLETE)
- RNDZ XPNDR ACTIVATION & SELF TEST
cb RNDZ XPNDR FLT BUS - close (veri f v )
RNDZ XPNDR - HTR for 24 min(l min if self test onl^)
RNDZ XPNDR - PWR , , , ,
SYS TEST (Lh) - XPNDR; SYS TEST (rh) - A (RRT XMTR OUT PWR)
SYS TEST ind -> 1 vdc
-24-
"SYS TEST (rh) - B (RRT AGC SIG); RNDZ XPNDR - TE
SYS TEST ind - >1 vdc o
RNDZ XPNDR - OPERATE; SYS TEST ind - 0 -4.5 vdc
SYS TEST (rh) - C (RRT FREQ LOCK) ^ ^ ^ ^
SYS TEST ind - <.8 vdc unlocked, > 4 vdc locked
SYS TEST (rh) - B
100:20-
-HAND CONTROLLER ADJ/ ARMED; THC POWER - ON
SIMPLEX A RCV ONLY - B DATA
RECORD, FWD, LBR (AS REQUESTED BY LM)
-GDC ALIGN to' IMU
- ORDEAL (V83) (R=R=0) , v
/lll02\
'\Xllll/’»
^SC CONT - SCS; LOAD DAPUlllir* ^4
DOCK PROBE CB(2)-1N ^ ^
BMAGS-ATT 1/ RATE 2
, START 16MM CAMERA r-p
^ UNDOCKING (100: 15: 00 )(0, 13/14, 0)_
AUTO RCS SEL - B3 - MNA
DV CG-CSM C4 - MNB
RR XPNDR-PWR(VERIFY)
V64;ACQ H6A
PHOTOS: COLOR TV
INSPECT LM
(LM 360° YAW)
INSPECT
UNDOCK
100:30-
- 25 -
-26-
P52 (OPTION 3)
T TORQUE
( 101 : 00 )
(0,176/39,0)
— GDC ALIGN TO IMU
VERIFY ORDEAL (V83)
— POO; MCC-H UPLINK
CSM AND LM VECTORS
CONFIRM PROPER SOLO CONFIG
ECS HOSES, COUCHES
CAMERA, STOWAGE
PANEL 10 SET FOR RELAY
MASTER ALARM AMPLIFIER - RIGGED
MEMKAR
\ ♦
OIPHDA
■»
ALPHHRATZ
( 100 : 56 )
(0,38,0)
SYSTEM CHECKS PRIOR TO LOS
-IIIIIIIIIIHII
= 101:26
= R= 1.84
= R= 2.9
liiiiiiiitniiir
-27-
101 : 3c
.VHF SIMPLEX A - REC ONLY - B DATA
(RECORD, FWD, LBR)
-P20 AUTO MNVR TO SXT TRACK (67°) (0,217/332,0)
LM DPI (101:38:48)(-72.7,0» 5)
VHF B - DUPLEX RANGING - ON
VHF RCV ONLY - OFF /
COMPUTE ROOT FOR LM
■ CONFIRM LM DOI (0,214/321,0)
P76 (ADD: 20 SEC); V82 (LM R2=2)(60X9)
-P20 AUTO MNVR TO SXT TRACK (TRIM) (0,224/313,0) = 101:42 =
= R= 3.67 =
: 70.2 =
siiiiiiaiiiiiir
START CAMERAS REMOTE OPERATION
INITIATE OPTICS TRACK ONLY
•V93;V57; V87
P20
(101:44)
(0,224/313,0)
-•iiiimimii-
= 101:57 =
=R= 13.02=
=R= 68.7 =
-28-
i02:oo-
6/23
P20
^ ( 102 : 00 ) ^
(0,289/327,0)
.02:30-
-POO; V64; AGO HGA (0,343/332,0)
-P20 AUTO MNVR TO SXT TRACK (TRIM)(0 ,349/330,0 )
5 102:12 =
sR= 34.00=
= R=241.1 =
P20
( 102 : 20 )
-GO/NO-GO PDI ABORT (0,350/327,0)
■S BAND SQUELCH - OFF (CONFIRM)
r 102:27=
=R= 84.40=
-29-
102 : 30 -
6/23
“POO; V48 (^xiflV ’ (0,140,0)
- OPTICS - RESOLVED/MED/ZERO-OFF
TRACK LM MANUALLY
(EVENT TIMER START)
_ ^|LM PDI (102:35:14)1
TROCEED; PITCH DOWN -.2®/SEC V
TO P52 ATT (0,206/80.0)
PDI
(0,18/310,0)
•SWITCH TO OMNI-C(AS REQUIRED)
-MSFN ENABLES S-BAND RELAY
|LM TOUCHDOWN (102:47-Tf)
MAN ATT PITCH - ACC CMD
-V44 SET LUNAR SURFACE FLAG
TOUCHDOWN
(0,282/180,0)
-KEEP PITCHING TO P52 ATT
VHF RANGING - OFF
VHF T/R (PANEL 9) TO RECEIVE
RR XPNR - OFF
V46;ST0P PITCH*,MAN ATT PITCH
- RATE CMD AT (0,206/80,0)
103:00-
- 30 -
6/23
31 -
-32-
i04:oo-
6/23
S/C CONT-SCS; MNVR +X BELOW HORIZON 2® (0,352,0)
POO; V48 /niOO\ ; V49 LOAD (0,330,0)
Vxini/
CMC - AUTO (0,338/352,0)
PRO - PRO
MAN ATT (PITCH) - ACCEL CMD
P22:
RESOLVED - MED - ZERO - CMC
F 06 45 (R3=MGA)
PRO
F 05 70 LOAD 10000
F 06 89 LOAD LANDING SITE
LAT
LONG/ 2
ALT
OPTICS ZERO - OFF; PRO
06 92 SHAFT, TRUNNION
OPTICS MODE - MAN
F 51
NOTE: POSSIBLE ALARM
407 IF TRUN>50®
RECALL 06 92
AND RESET WHEN<50®
/take 5 MARKS 30 SEC APART
(HOLD AT F 06 49 FOR 30 SECJ
NM (N OR S)
LONG/2 alt
04:30-
104 : 30 '
6/23
s iniuimimima mil Bii ii
34
-35-
105:30 — t
10 5*
-25 -
105 : 50 —
106 100 1
MNVR AS REQUIRED FOR PHOTOGRAPHY
P=0
ROLL AS REQUIRED
V37E 21E
F 04 06 R1 00002, SPECIFY VEHICLE
R2 00001, CSM
PRO
F 06 34 GET LAT, LONG
LOAD DESIRED GET
PRO
F 06 43 LAT, LONG, ALT
(RECYCLE) V32E TO 2 (INCREMENT GET 10 MIN)
(EXIT) PRO
6/23
P00;V64;ACQ HGA
MCC-H UPLINK CSM S/V AND TARGET LOAD
RECORD PLANE CHANGE MNVR PAD
- 37 -
6/23
- 38 -
107 : 30 .
- 39 -
iiiiimBiiiiiiiiiiiiiis: </} li- ziiiiiiiiimiiiiiiiiuiiiiiiigigiiiitMiiiiiiiiiiiimi
-40-
LM INSERTION (124:30:39:
— VHF RANGING LOCK ON; RELAY R TO LM\ /
rAUTO MNVR COMPLETE (0,202/73,0)
V48 /11102\ I
Ixmi; (124
^ ' / r\ ^
ALDEBARAN
— P52 (OPTION 3)
(124:36)
(0,72,0)
*
' MENICAR
^igiiiiBigiggs
= 124:35 s
■8=251 .7 E 05
=R=-43Q.5j
_P00;V64; 93
MCC-H UPLINK LM VECTOR
ZERO OPTICS
— REQUEST LM TURN ON
TRACKER LIGHT T TORQUE
— P20; AUTO MNVR TO SXT TRACK (TRIM) (0,232/73,0)
6/23
P32; LOAD
PRO TO N45
JIF VHF; V93; VHF ONLY |
t IF NO VHF; V88; SXT ONLY I
I 1
CSI TIGN
400001, +208.30 +130.00
30.00 N,.ELEV,
TP I TIGN
P20
(124:44)
(0,232/73,0)\
V93 (NOT BEFORE 5 SXT MARKS PROCESSED)
STOP SXT MARKS
-V88 ; PRO ON V51
V90(R2=2) (N16=CSI TIGN) VOICE LM Y DOT TO LM = 1
V90(R2=1)(N16=CSI TIGN) CSM Y DOT= I ^
V87
V16N45
-41-
1 ’ 25:00
SYSTEMS CHECKS AND EVENT TIMER
PRO ON N45 75 I
LOAD N81 VGY WITH (-) CSM YDOT
BU S TIES 82 1 ^ —
P40j AUTO I a_J — ! s ^
MNVR (76°)'(0, 156/269,0) V56 {TERMINATE P20)
-COPY LM CSI SOLUTION-^ . T
S PS CHECKLIST 84 j *
= ■ 125:05s
= R=165:41 =
sA=-l 39.01
.AH
AT-CSI/CDH
' AT-CDH/TP]
j, JlAVCS i -LV
"T IaV CDH-Lli
[LM CSI (125:21:20) (49.4, 0, 0)
~ |CSM CSI (125:21:20)^ 49.9,0,0) ;
P76'(ADD: 23 SEC) ^(0 J 80/269 , 0 )
V82(LM R2=2)l(45x45)
BUS TIES
P20; AUTO MNVR TO SXT TRACK ( 30° ) ( 0 , 228/ 2 99 , 0 )
125:30
V57; V87
-42-
r PRO ON V51 AFTER 3 MARKS PROCESSED
V 67; load N99 {+02000 ,+00020 ,+00001)
i V57
^ VI 6 N45
siiiiiiiiiiiiQ
a 125:36s
=R= 113. 7^
|r=-129.1 =
apiiiiiiaiiiii-
125:40
PRO ON V51 |— 1 — — ^
jV88 OBTAINLM PC TIGN-»16 | ! I ^ ^ !
V90(R2=2) (N l6=PC TIGN)VOICE LM Y DOT TO LM
COPY LM PC P76 PAD— ^ ^ T T
-V57; V87 ‘ .
V16 N45 33 . ! I ‘ . !
-30
125:50
SIF NO PLANE CHANGE CONTINUE MARKS
5 PRO ON V51; V88 P
^P76 LOAD LM PC BURN DATA
1 LH PLANE CHANGE (125:50;40)(0, 226/228,0)
P76 INCORPORATE
-T— P20 V57; V87
V93 AFTER THREE MARKS PROCESSED
-43-
126:10
M
-6 -! N
0
126 : 20 '
126 : 30 -
+ 32 -*
SETUP -
,M CDH P76
84
33
-^LM CDH (126:19:40)(-1 .9,0,4.! )
CSM CDH n 26 : 19 : 40 :( 2 . 2 . 0 ,- 2 . 7 ) )
P76 1(0,239/1 60,0)
■ P20; AUTO MNVR TO -SXT TRACK( 27° )(O,232/133,0)
iV57; V87
V93 (AFTER 3 MARKS)
CONTINUE MARKS UNTIL SUNSHAFTING)
PRO ON V51 07 1 I T"
StaiiBBiiiiBiittt;
s 126:26 =
s? = 69.91 =
iR =-119.8=
aimiBiimiiC
PRO ON V51 37 e o ■ TPI TIGN
_^4 (ELEVATION 55 + 0 OOOO |+208 . 3 ol+130 . Oo[ N ,ELANG , WT
ANGLE OPTION) PRO ON N45
aiiiBBiiaiD
- 44 -
*
• •
-45.-
i27:oo-
6/23
V93; V57; V87
'NOTE: DO NOT KEY V93 IF|
I SXT OR VHP ONLY [
■umiiiiiiiiDmEi
i 127:T1 _ i
s R = 17.19 s
s R =-104.9 =
SlIEBRIIlIBBailllS
V88
PRO ON V51
P35 FINAL COMP —
UpRO at TPI +12)
-COPY LM MCCl (P76)-
P41 (BYPASS
AUTO MNVR) '
-IMCCI (127:13:27) I
(0,266/18,0)
P76; P35 AUTO MNVR TO SXT
TRACK (TRIM)
P93; V57; V87'
COPY CSM MCCl SOLUTION
I NOTE; DO NOT KEY V93 IF SXT OR VHF ONLYf
SI I V93 AFTER 3 MARKS PROCESSED
^
COPY CSM MCC2 SOLUTION
' V88 -0
1 PRO ON V51
■s P35 FINAL COMP
(PRO AT TPI +27) —
la. MCCl+12 33
.COPY LM MCC2 P76 PAD ,
_ P41 (BYPASS AUTO MNVR)
MCC2 (127:28:27) (0,300/7,0)
P76
-POO; V89 (R2=2), AUTO MNVR TO
,COAS TRACK (37^) (0,275/330,0)
-46-
127 : 30 -
16 RCS JETS - ON
P47; V83 AT R = 1.25 N.M.
BRAKING GATES
SfiiiimimuS
S 127: 26 =
= R = 5.60 =
S R =-52,2 =
niiiiiiimiiiK
RETICLE
R(FPS)
R(FT)
R(N.M.)
ANGLE (DEG)
30
6000
1.0
.13
20
3000
.5
.26
10
1500
.25
.54
5
500
.08
1.6
Siiiniiiiiiiic
300
.05
2.7
= 127:41 =
= R = 0.06 =
200
.03
4.0
: R =-12.3=
100
.02
8.5
=ninflmiimE
127:50
TPF (127:40:38)
DOCK CHECKLIST;
CB DOCK PROBE (2) - IN
CB SECS ARM (2) - IN
PROBE RETRACT -VERIFY
SECS PYRO ARM A AND B - ON
4 QUADS - ON (8 T/B - GRAY)
CMC - AUTO
AT CONTACT;
CMC MODE FREE
NULL RATES
BOTTLES PRIM (2), SEC (2)
128:00
-47-
5.0 NOMINAL MAOOR PROCEDURES SUMMARY
The following sections present a summary timeline and
checklist of major CSM activities during the nominal
Mission G LM active rendezvous. The timeline in Section
5.0 will aid in interpreting the data included in the
onboard rendezvous checklist and serves as a time cor-
related table of contents for the nominal detailed
procedures which follow in Section 6.0. In addition.
Section 5.2 includes a one-page summary checklist for the
nominal mission.
5,1 SUMf^APY timeline
-48-
GET EVENT PHOG
(99*10)
iMCC-H UPLTNiK CSM (pOO)
StATE VECTOR
transfer this vehicle state vector
TO OTHER VEHICLE STATE VECTOR (V66)
copy CSM SEP PAD
•DON HELMET and GLOVES
(99+16)
•SC CONT « SCS
PATE - LOW
ATT 00 - MIN .
LM PCS COLO FIRE CHECKS
(99+20)
DISABLE CSM roll 4ETS
RATE - high
atT oh - max
(99+21)
LM PCS HOT FIRE CHECKS
(99+22)
enable a/C and B/D poll
(99*25)
VERIFY auto pcs SEL
-C4(-PlTCH-X)-0FF
■*03 ( + YAW««X) »0FF
FOR LM RR SELF TEST
VERIFY RNDZ XPNDR-HTR
(99*27)
LOAD .DAP WITH GROUND UPDATE
(21111) (36427) (-00089)
(Xini) (33657) (+O0032)
GET , event prog
(99+32)
LOS
display TOTAL ATTITUDE ERRCR(V62)
SC CONT - rMC
CMC MODE - AUTO
AUTO MNVR TO { 0, I4t 14) (V49)
(INERTIAL SEP ATT EXCEPT YAW)
(99+35)
configure camera
(99+42)
SUNUP
(99+51)
CMC MODE-FREE (AS REOO FOR LM
AGS CALIR)
CMC MODE-AUTO (AFTER 32 SEC)
verify max D8 for AGS CALI-B
perform SYSTEMS CHECKS AND
Switch verification
WA lT For Lm to compute ags align
AND GIVE eot THEN
YAW 14 DEG left AFTER LM AGS
CaLIB (0» 313/14t 0)
(99+57)
pND2 XPNDR CHECKS
(100+07)
hand Controllers aoj/armed
THC POWER-hN
VHF A-SIMPLEX
VHF RCv only-b data
TApE recorder-fwd
pCm bit rate-low
MISSION G summary TIMELInE
-49-
GET event PRo/5
( 100 * 10 )
GDC align to IMU
(lOO+ll)
verify ordeal (VR3)
(100*13)
Sc CONT-SCS
reload OAP (11102) , (V46)
(xmi>
BMAG MOOE - ATT 1/RATE 2
wgS (100*15+00)
Ott*# «« -ft ■» -tt «« »»»««<*# -ft «
UNDOCKING (Of 13/U, 0)
fHMH* « * •»•»#« ■»
AUTO RCS <;EL-.ti3-NNA
C4-NNP
DV CG-CSN
RMUZ XPNOR Fl»R-P>^R (VERIFY)
(100*19)
AOS
ACQUIRE HCjA (Vb4> (POo)
activate color Tv
TAKE PHOTOS
inspect LM during lM 360 deg yaw
(100*32)
set EMS= 102.5
(100*34)
BMAG MODE - RATE 2
Sc CONT-CMC
CMC mode - AUTO
-•5 (100*35)
external nv targeting (P30)
load VGZ = -2.5
GET
event
PROG
(100*37.)
RCS THRUST
PROGRAM
(P4] )
AUTO MNVR
(tRim)
TO BURN ATTITUDE
(100+3S)
rCs thrust
SETUP
(P41)
(100*39*58)
CSM separation <0* 0» -2.5)
(0» 90/l4» 0)
«<»««*»■»■«■•» fHHHt «»««««» iMMHHH*
(100+44)
rendezvous NAV program (P20)
AUTO MNVfl TO SXT TRACK (42 DEG)
(0il48/56i0)
VHF 0-OUPLEy
vhf ranging-ranging
monitor LM RR checks
compare EMS vhf and V83 RANGE
perform optics checks
(100*52)
COPY DOI P76 PAD
COPY PDII ♦ 12 P76 PAD
COPY CSM rescue PAD
(100+54)
SUnDOWN
( 101 + 00 )
iMu realign TO REFSMNAt (P52)
(OPTION 3)
COPY Gyro torque angles
( 101 +oS)
GDC align TO IMU
verify 0PDEAL(V83)
MISSION G summary TIMELTNE
GET
EVENT
pROG
(101*10)
MCC-H UPLINK CSM AND LM
stATE Vectors
(pon)
(101+26)
(101+28)
(101*31)
SYSTEMS check PRIOR TO LOS
LOS
VHF A-SIMPLEX
VHF pcv ONLV-b Data
TAPE RECORDER-FWn
PCM BIT RATE-LOW'
(101*33)
RENDEZVOUS NaV PROGRAM (P20)
AuTO MNVR to SxT track <67 DEG)
(0,?17/332»0)
< 101 * 38 * 48 )
LM UOI (-72.7,0,14.8)
VHF 8-DUPLEX
VHF RANGlNG-RAAieiNG
VhF RCV only-gfp
COMPUTE ROOT FOR LM
( 101 * 40 )
SUNUP
( 101 + 42 )
confirm LM uci
TARGET Dv program (P76)
(Ann 20 SECONDS)
LM ORRIT parameter display (V82)
(60X9)
MISSION G summary riMELTNE
GET
event
PROG
(101+44.)
rendezvous NAV program (P2(»)
Possible auto mnvr to sxt track
(TRIM)
(0i2Z4/313,0)
(101*49)
start cameras remote operation
initiate optics track only
001*52)
reinitialize W MATrIX(V93)
call marking routine (V57)
SET VHF RANGE FLAG (V67)
O 02*07)
terminate marks
(102*17)
aOs
acquire HGA (V64) (POO)
(102+19)
rendezvous NAV program (P20)
aUto mnvr to SXT Track (TRIM)
(0* 352/330* 0)
( 102*25)
obtain go/no go fop poi ABCRT
(102*27)
confirm s-band squelch-off
(102*32)
rElOaU DAP(HIOI)
(Xllll)
AUTO MNVR TO (0* 140* 0) (V49)
(102+35+14)
maintain lm in SXT field of VlEw
# -ft**** ««***«■«« *HH» «*»»« «• *«■»«<*•» «**
lm Pul
*t *H» »*•»■»*•»■»««««•»***•»# «« * <*
-51-
GET event pHnG
(102*36)
PRO {PITCH Down at ,2 OEG/SEC To
P52 attitude)
(102*43)
SWITCH To OMM-C{a<; REQUIRED)
(102*46)
MSFN enables S-BanD relay
(102+47+11)
ft iHMMHH}- »-»»««««« tt 0 »»###«# #
LN touchdown
^'AN ATT (PITCH) - ACCEL CND
(102*53)
sundown
set lunar surface Ft A6 (V44)
(102*55)
vhf pangimg - oFf
VHP T/R - receive
(102*57)
PR XPNDH-OFF
STOP PITCH rate
hanual ATT(Pr(CH> , rate CMD
AT PITCH angle OF rO DEG
(Of 206 / 80 » 0 )
(103*01)
IMU realign to REFSMWAT (P52)
(Option d
COPY gyro tor(juing angles
(103*07)
■GDC align
(103*09)
verify 0RDEAL(VB3)
get event PROG
(103*17)
COPY P22 PAD INTO CHECKLIST AT GET
time of 104*25
(POSSIBLE P27 UPLINK OF RLS AND
CSM STATE VECTORS)
(103+22)
mnvh To nsfn suggested attitude
systems CHrCKS PRIOR TO LoS
(103+29)
LOS
(103+39)
SUnUP
(104*01)
SC CONT * SCS
PNVR *X AXtS to 2 DEG BEL0l<
Horizon <o, 352 * o)
CMC idling program (POO)
reload DAP(lllOO)
(xnii)
AUTO MNVR TO(0,330,0) (V49)
(104+07)
CMC MODE - AUTO
PRO(STaRT MNVP)
^AAN ATT (PITCH) - .ACCEL CMC
ORBiT NAV program (P22)
(TAkE 5 marks 30 SEC APART)
(104+15)
AOS
(104*43)
CMC IDLING PROGRAM (POO)
man ATT (PITCH) - rate CMD
reload DAP (lilOU '
(XlllU
AUTO MNVR 10(270,101,45) (V49)
MISSION G SuMVARV TIMELINE
GET
event
phnc-
(lOA+51 )
SUM’iown
(lOA+55)
AC^^UIHE HGA (Vfe4)
a04<-57)
FOAI SW 2 - INEHTIal
a04*B9)
FCC-H UPLTNK (P2?>
(Plane change HEFS^'<f^AT)
(105*04)
CMC mode - free
IMU realign to HEFSMMAT (P5?)
PLANE CHANGE HEFSmmAT
(OPTION n
GYRO TONQUING
(105*08)
CMC mope HCLU
(105+11)
GDC align
(105*12)
initiate eat FEHlOn
(105*27)
SYSTEMS CHECKS PRIOR TO LOS
(P21 IF OESIHEU)
(105*27)
LOS
(105+37)
SUNUP
MNVR AS REOUIHEQ FOP PHOTOGRAPHY
(106*13)
AoS
MISSION 6 SUMMARY TIMEUnE
PROG
GET event
(106+15)
AC(3UIHE HGA (V64) (PUO)
mcc-h uplink csm state vector and
Target load
record plane change mnvr pad
(1 06*37)
AUTO MNVR TO (O 9 0* 0) (V49)
COaRSE align CDU (V4l)
load N92 with pad SHAFT ANC
TRUNNION
pRO
(106+50)
sundown
star Check
(106+52)
external DV targeting (P30)
(106+56)
rUrN attitude MNVR (P40)
(106+57)
SPS THRUST SETUP (P40)
(107+05+34)
CSM PLANE CHANGE (0+ 16,6,0)
( 0 » 0 , 0 )
0 « « -tMHMHH* « «» tt e *
(107+08)
ACQUIRE HGA (V64) (POO)
MCc-H UPLINK (P27)
(LIFT-OFF REFSMMAT)
(107*10)
AUTO MNVR TO (0, ‘45* 0) (VA9)
after mnvr complete
CMC mode - FREE
- 53 -
EVE^T
Get ewent
(107 + U)
IMU PEALIGN TO (P52)
LANDING SITE RtFS^MAT
(OPTION n
GYRO TORQUInG
(107+17)
CNC MODE - hold
(107*18)
GDC align to IMU
(107+195
OROEAL (VR3)
(107+255
LOS
(107+265
begin rest and Eat period
AUTO MNVR TO REST ATTITUDE
GET
( 124 + 00 ).
acquire HGA(V64)
PROG
(POO)
vHf configuration chcck
VHP 8 - DUPLEX
VHF T/R - RECEIVE
VHP ranging - ranging
( 124 + 02 )
reload dap (lllOl)
(X11115
( 1 24 + 03 )
AUtO MNVR TO (0, 206» 0) (V49)
(124+10)
confirm S-BANO S(3UELCH"0FF
(124+12)
msfn relay disabled
(124+15)
aUTO MNVR TO (0* 73» 0) <V49)
start MNvr at lift-off
(124+23+25)
pRo (PITCH DOWN AT 2 OEG/SEC TO
P52 ATTITUDE)
lift-off
^ ^
(124+30)
SWITCH To OMNI A(AS REQUIRED)
( 124+30 + 39)
LM userti;;^n
(124+32)
VHF hanging lock On
rELAY root to LM
MISSION 6 Summary timelime
event
phOG
.37
■32
(124+34)
(124+35)
(124*36)
(124+40)
(124+42)
(124+44)
(124+47)
024+49)
(124+54)
AUlO MNVP COI^PlETE (0, 20?/73, 0)
FPLOAO dap (U102)
oaiU)
IMU realign to REFSMf^AT (P5?)
(OPTION 3)
COPY GyRO TOPOUE ANGLES
SUNDOWN
mcc-H' uPlink lm state VECT0R(P«0)
request LM TLRN On tracker LIGHt
RENDEZVOUS NAV PROGRAM (P20)
AUTO MNVR to SxT track (TRIM)
(V»232/73»0)
CSI targeting PPOGRAP (P32) (P2o)
LOAD CSl TARGtTiNG PATA
reinitialize w matrix (V93)
SET VHF range flag (V87)
CALL marking H0UT1nE(V57)
after five sx( marks processed
RFIniTIALZE w matrix (v93)
TEHMINATE SXT marks
MISSION G summary HMELIME
-54-
GET event PR(-G
(124+59)
terminate VHF marks (V88)
OUT OF PLANE DATA (V90)
(CSM AND LM)
VOICE LM Y DOT TO LM
SET VHF RANGE FLAG (V87>
(125+00)
LOS
-I? (125+09)
TERMINATE VHF MARKS
CSl targeting final comp (P32)
COPY CSM C5T SOLUTION
load N81 VGY WITH(-) CSM YCOT
-8 (125+13)
SPS THRUST PROGRAM (P4d)
terminate PPO (V56)
AuTO MNVR TO BURN ATTITUDE
(76 DEG) (0» 156/269, 0)
-6 (125+15)
COPY LM CSI PAD
SPS IHruST setup (P40)
(1 (125 + 21 + 20)
tt « -It «
LM CSl (49.4,0,0)
««« «««««««««
CSm CSl (-49.9,0,0)
(0, 180/269, 0)
target dv Program (p76)
■<ADU 23 SECONDS)
LM orbit parameter display (V82)
(45X45)
-55-
get EVENT PROP
(125+22) -27
SUMJP
(125+27)
RENDEZVOUS NAV PROGRAM (P20}
AUTO mNvr TC SXT track (30 DEG)
(O,220/299»O)
^51 (125+29)
CALL marking R0UTINE(V57)
set VHF range FLAG(V87) -24
(225+32)
after three marks PROCESSF.n» Vb7
load N99(+o200O»+O0OH0, +00001) -15
CALL marking HOUTINf (V57)
(125+A3)
Terminate vhf marking ( vbS)
COPY LM PC TI6N -10
out of plane UATA(V90)
VOICE LH YDOT to LM
COPY LM PC PAD -6
(125+45)
CALL marking H0UTINE(V57)
-.30 (125+50)
terminate marks
load target DV program (P76)
•29 (125+50+40)
■» fl.# « -tM* «
LM plane change 0
■B
incorporate P76 OATA
MISSION G summary TIMELIME
GFT
event
PROG
(125+53)
RENDEZVOUS NAV P ROGRAM (P2d)
POSSIBLE AUfo^NVR TO SXT TR^CKT'
(TRIM)
call marking R0UTINE(V57)
SET VHF RANGE FLAG (V87)
(125+54)
aOs
(125+56)
AFTER THREE MARKS PROCESSED
reinitialize W matrix (V93)'
(126+05)
terminate marks
OUT OF PLANE DATA(V90)
VOICE LM YoOT to LM
(126+10)
CDH targeting final comp (P33)
COPY CSM CDH SOLUTION
(126+14)
RCS thrust program (P41)
Bypass burn attitude mnvr
For Small burns
terminate P20 (V56)
RCS thrust setup (P41)
( 126 + 16 )
COPY LM CDH PAD
(126+19+40)
B B •»«» B «■ B B «*«• B ««■«•«•«■ B .JHHHHI. «■ -tH* B B
LM CDH(-1,9,0,4.1)
B 4 B A « 4 B * B * B * 4 B B « * «■ 4 4# A ■» « ft « <HH»
bBbBBBBBBBbBBBBBBBbBBBBBBBBBBBBBBB
CSm CDH (2 .'2,0, '-2. 7)
(0. 239/160* 0)
BBbBBBBBBBbBBBBBbBbBBBBBBBBBBBBBBB
GET
event
PHOG
target DV PRcGRAf^
(P76)
♦ 25
(126+23)
RENDEZVOUS NAV PROGRAM
(P20)
AllTO MNVR TO SaT track (27
DEG)
(0,232/133*0)
(126+24)
CALL MARKING H0UTUF(V57)
set VHF range FLAG(vR7)
+29
(126+27)
after three marks processed
reinitialize W matrix (V93)
♦32
(126*30)
TPI targeting program
(P34)
(ELEVATION angle OPTION)
♦ 36
(126+34)
CALL marking routine (V57)
♦39
(126+37)
COPY LM TPI TIgN
♦47
(126+45)
terminate marks
♦ 40
(126+46)
Tpi targeting program
(TIGN OPTION wlTM LM TIGM)
set mdc event timer
(P34>
♦ 53
(126+51)
SpS thrust PROGHAf^ (P40)
TFHMIMATE PHO (V56)
AUTO MK*VR TO HURN ATTlTUDtr{52 DfO
(0,191/5*0)
COPY LM TPI P/6 PAlj
♦55 (126+53)
SpS thrust SElUP (P40)
MISSION G SUMMARY TIMELINE
56-
E^ENT
PHOG
0 ( 126 * 58 + 27 )
* tt « -tt »
LM TPi {21 .q,-*1»-U.0)
««« *H* « ««•»■»«*«■«■««# -IHHt * «
tt tt iMj *Ht ft ■»•»#»«■»«•*«■»■ ■»«««•» «•
CSM TPI (-22.3,0.1,10.9)
(0, 200/5* 0)
<M* *« *H* «*■» iHHKMt ■» »
target DV program (P76)
(AUO 12 SECONDS)
(126+59)
rendezvous NAV program (P20)
AuTo MNVR TO SXT TRACK 04 OEG)
(0* 248/39, 0)
mCC targeting program (P35>
+4 (127+02)
reinitialize W matrix (V93)
call marking ROUTREtVS?)
SET VHF range FLaG(v87)
(127+06)
los
+1? (127+10)
terminate narks
mcci Targeting final comp (P3b)
COPY CSM MCCl SOLUTION
COPY LM MCrl PAD
(127+11)
RCS thrust program (P41)
Bypass burn attitude mnvr
-57-
get EVENT pRor;
«15 n27*13*27) +32
LM MCCl
iMt •»«•»•» <mhhhhmhhh»<h+ ««■»«••»•»•» »«■»#■»«« +38
« »« » «MHt » « ■» o « « « iHHHHHMm * tt *
CSM MCCl (0» 0)
•»■»«•»■»«■»<»<»«•»«« o <HHH» «*«• <HKHt •«•*#
(127+14)
Target dv program (p?6)
MCC2 TARGETING PROGRAM (P35)(P2Q)
POSSIBLE aUtO MNVH TO SXT TPACk
(TRIM)
+18 (127+16)
reinitialize W MaTrtX(V93)
CALL marking R0UTInE(V57)
SET VHF range FLAG(V87)
(127+21)
SUNUP
+27 (127+25)
TERMINATE marks
FCC2 targeting MNaL COMP (P3B)
COPY C5M MCC2 SOLUTION
COPY LM MCC2 PaU
+20 (127+26)
RCS THRUST program (P4i)
rypass burn attitude MNVR
+30 (127*28+27)
« tt «t *■»•»■» -IMHH* ««•!♦««««•» 4H* -tH+ ««■ tt *»■»«. tt »
LM MCC2
«H» «« -tHHf •+•» +Ht »««»<»■»•»«•»■» tt tt * «"ii «■
«««■»■»■»•»«•»■»•»*«««<>■» tt O «•»■»«#« ■»
CSM MCC2 (0» 300/7, 0)
•»# « -tt ■»'»•»•»•»«*■»*«««««■»»«•««• W •»«■»» tt
TARGET DV program (p76)
MISSION G Summary timeline
(127+30)
AUTO MNVR TO COAS TRACK ( V8S )( PO 0 )
(37 OEG) (0»275/330»0)
(127+36)
thrust monitoring program (P47)
(KEy V83 and monitor LM BRAKING)
« Braking gates and ret ang»s *
« *
30fPS at 6000FT, (I.OONM) -,13 OEG ^
« ?0FPS AT 3;00FT.( ,50NM)*;26 OEG «
<» lOFPS AT 1500FT,( ,25NM)-.-54 DEG ^
sfPs at
500FT,( ,25NM)-.-54 DEG
SOOFT.( ,o 8NM)-1.6 DEG
300FT,( .05NM)-2.7 DEG
?00FT.( •03NM)«»At0 DEG
10QFT.( ,02NM)-8.5 OEG
■tt* «"»* «■ » ft tt 4HH» <»***♦*«■■»■■»•■'»■ ••+ «
(127+40+38)
«««ft«ft«ft«««tt««««a««<»ftftft«ftftftftftftftftftft
TPF
SaHKARir CHECKLIST
FOLDOUT FRAME (
foldout frame <X-
FOLDOUT FRAME
-59-
6.0 NOMINAL DETAILED PROCEDURES
The folTowing four sections contain 1) The procedural ground
rules assumed when generating procedures, 2) The detailed
nominal procedures, 3) A summary of the rendezvous navigation
schedule including the angle between the LOS to the Sun and
LOS to the LM, and 4) A Summary of the inertial roll gimbal
angle and the ORDEAL pitch and inertial pitch gimbal angles
during the nominal G Mission.
6.1 Procedures Ground Rules
6.1.1 The CSM will be targeted for the same TIGN as the
LM for the CSI, CDH, and TPI burns.
6.1.2 The CSM will obtain from the LM the CSI, CDH,
and TPI times utilized in the LGC targeting pro-
grams. These TIGN's are loaded into the CMC targeting
programs .
6.1.3 LM burn data will be incorporated into the CMC
LM state vector using Program P76 following each
LM burn. No attempt will be made to account for
LM burn residuals. The LM burn TIGN loaded in
Program P76 will be biased by a fixed number
simulating an impulsive LM burn. The non-zero
LM burns considered and the corresponding bias
times are DOI (20 Sec), CSI (23 Sec), and TPI
(12 Sec).
-60-
6.1.4 The CSM vfill compute using V90, the out-of -plane
velocity of the LM prior to the CSI , Plane Change,
and CDH burns for use in the LM targeting pro-
grams .
6.1.5 The ordeal setup on FDAI 2 will be verified
approximately once per orbit.
6.1.6 The GDC will be aligned to the IMU prior to each
backup CSM burn.
6.1.7 No burn attitude verification using stars or
the horizon will be made in the CSM.
6.1.8 The PI PA bias determination, EMS DV test, and
EMS accelerometer check, identified in the AOH
as required before each SPS burn, need be
scheduled only prior to the entire rendezvous
sequence.
6.1.9 The SM RCS propulsion check identified in the
AOH as required before each SPS burn, should
not include recording the values monitored.
6.1.10 It is assumed that the CMP is able to move to
the LEB or command seat during automatic
attitude maneuvers and the time required to
move is less than oneminute.
6.1.11 The procedures contained herein reflect the
COMANCHE 44, 45 programs and routines.
-61-
6.1.12 The minimutii times to be allowed for the CMC
programs are:
A.
P52
5 Min.
B.
P76
1 Min.
C.
P30
2 Mm.
D.
P32
Final
Comp
3 Min.
E.
P33
Final
Comp
3 Min.
F.
P34
Final
Comp
3 Min.
G.
P35
Final
Comp 1
.5 Min.
H.
P41
(Excluding ATT
RCS Setup) 1
Mnvr and Including
.5 Min.
I.
P40
(Excluding ATT Mnvr and Including
SPS Setup) 5 Min.
i
6.1.13 All automatic maneuvers (DAP) are made at a
rate of .5 Deg/Sec after LH Insertion.
6.1.14 The state vector of the active vehicle (LM)
will be updated in the rendezvous navigation
Program, P20.
6.1.15 The SXT navigation mark frequency during a
tracking period is one per minute.
6.1.16 Recycles for CMC targeting Programs, P32 and
P33, during mark periods have not been
scheduled. They will be included, as desired,
for solution comparison purposes, when they
do not preclude taking the minimum number of
SXT and VHP marks prior to a burn.
-62-
6.1.17
6,1.18
6.1.19
6.1.20
6 . 1.21
6 . 1.22
6.1.23
The delta time between the PRO for Final
Comp in Program P35 and the MCC is three
minutes .
Program P20 will be terminated (V56) in
the thrust program prior to each backup
CSM burn. This will necessitate calling
Program P20 after the burn in addition to
a pre-thrust program. Exceptions: In-
sertion (POO does it) and the MCC burns.
The automatic star selection routine in
Program P52 will be used during each IMU
real ignment.
The CSM attitude has been specified to be
compatible with HGA communications when
no other attitude constraint prohibits HGA
coverage.
The G1 onboard checklist should closely
resemble the F onboard checklist.
The SPS gimbal motors will not be activated
for a CSM backup of a LM burn until the
CSM knows it must become active.
Backup charts for the CSI, CDH» TPI, and
MCC burns will not be used in the CSM.
-63-
6.1,24 VHF navigation marks cannot be taken at
ranges greater than 327 nautical miles.
6.2 detailed procedures
« «
* MISSION e RENDEZVOUS PROCEDURES «
« *
#*#*#*** -IHMHHHMI* « «*«<♦***<>■»•» *■»««■# fl. «
assumed initial switch settings *
ftftCOR SWITCH SETTRGSftft
CMC ATT-It^U
PDA! SCAlE- 5/1
FDAl SELECT-1/?
foaI source-att set
ATT SET-IHU
man ATT(3)-RATE CMD
LiMiT CYCLE-OFf
ATT DH-MAX
rate-low
THC-LOCKEO
RHC-LOCKEC
TRANS COnT PWR-ON(UP)
ROT CONTR PWR \nRMAL-l OFF»?
AC/OC
ROT CONTR PWR direct (BoTH>-
OFF
SC CONT-CMC
CMC MODE-AUTO
BMAG mode (3)-RATE2
SPS thrust OTRFCT-NORmaL
UV thrust (A tB) «OEF
scs Tvi; (roth)--rate cmd
SPS 6MDL MTR(4)-0FF
DV CG-LM/CSM
IMU CArE-OFF
EMS ROr’L-OFF
,05 G-LfF
LV/SPS IND (B0TH)“PC9SFI
TVC GMBL drive (BOTH)-I
FCSMUtB>-RESE7/0VERRI-CE
£MS FUNCTION-OFF
EMS MODE-STBY
UP TLM MDC(CM*IU)-BLOCK
pcs TRNFR-SM
panel 8 C8 CLOSED EXCEPT
RCS L0GIC(2)
DOCK PROBE <'2 )
ELS BAT A.BAT B
PL VENT FLT/PL
FLOAT 0AGI3)
SECS arm bat a,baT e
AUTO RrS SEL(16)-MNA
EXCfPT -CAUPITCH-X)-0FF
-83<+YAW«X)«0FF
TVc SERVO PWR (B0TH>-0FF
FOaI/GpI PWR-aCTH
LOGIC PWR 2/3-0N(UP)
SCS elect PWR-^GDC/ECA
SIG COnO/DRVR bias PWR(2)-AC1
MISSION 6 detailed PROCEnURES
-65-
BMa 6 PWR(Bu]H).nN
coaS pwr (LWiNn>-oN
fdai SWI-INERTIaL
FOAl SW2-0RB hate
EARTH/LUNAR-LUnaR
ALT SET KNOB TO AVE Al T
mode-opR/slow
«*UMP switch S£^T^^^,S<»«
6/N PWR-ACl
MN BUS Tl£(2)-nFF
NONESS 6 uS»0FF
panel 5 6/N CB (IO)-CLOSED
panel 229 CB CLOSED EXCEPT
MN rEL PYROC?)
<»«CMP SWITCH S£TTIN6S«<»
G/N PWR CPTiCS-ON
R/N PWR»IMU-ON
cont SPEEO-Lo
OPTICS MCOE-CMC
7ER0 OPTICS-ZEPO
RNOZ xpondek-off
CONT COUPLING^RESOLVED
SCT TPUN-SLAVe TO SXT
condition LAMPS-ON
UP Tlm(LEB)-ACCEPT
C/W-NORMAL
C/W-CSM
C/W-POWER
high gain ant TRACK-AUTO
high gain ant beam-wide
high gain ant PWR-ON(UP)
high gain ant servo-prim
MISSION G detailed PROCEDURES
-66-
»# #»«<» «HM» O * tt o «•»» <HHH» -»H» «« tt
^ *
» TIMELINEO RENDEZVOUS P«OCEniiflES »
♦ <»
Mt *#• O «■#»«♦« <H» ’»■»»•»««» e <H» « «
» PROCEDURES THRU UNDOCKING o
»«###*♦•»»»«««•#<»• <H» «*<♦«•»*■»•<»«■»««■«* <HMH* •»•»* ft « W
(99*10)
»«MCC-H UPLINK CSM state VECTOR***
POO KEY V37E00E
UP TLM(CP) (MDC)-ACCEPT
MONITOR UPLINK ACT LT-ON
monitor gnu uplink
MONITOR -UPLINK ACT LT-OFF
UP tlm(Cm) (mdc) -slock
confirm comp lt-off
key V66E
COPY separation pad
DON helmet and GLOVES
(99*16)
BMaG mode (3) -ATT1/RATE2
rate - LOW
ATT D8 - PIN
SC CONT - SCS
LM Res COLO fire CHEckS
(99*20)
AUTO RCS SEL-A/c*
8/D roll-off
rate - HIGH
ATT 09 - MAX
LM RCS HOT FIRE checks
auto RCS SEL-A/C*
B/D roll-mna
(99*25)-
verify auto RCS SEL
B3(+YAW-X)-CFF
C4(-PITCH-X)«0FF
for LM RR self TEST
verify RN07 XPNDR-HTR
(99+27)
**LOAO DApiHV
’key V48E
F 04 46 (DAP CONFIGURATION)
load
21111
^lU
PRO
F 06 47 (CSM and LM WT)
LOAD
♦36427
+936S7
PHO
F 06 48 (SpS 6MBL TRIM)
load
-00089
*00032
PRO
kEy V46E
KEY V62E
BMaG mode (3) -rate 2
SC ConT - CMC
CMC MOnE - AUTC
SET MDC ET counting DOhN TO
MISSION 6 detailed PROCEDURES
-67-
SEPARaTION tign
( 100 * 39 + 58 )
(99*32)
LOSS OF signal
<»«MANELiVER TO UnOOCKJNG ATTlTU0£-tt*
(INERTIAL SEP ATT EXCEPT lA
DEG YAW)
KEY V49E
F 06 22 (COMMANDED R»P,Y)
load (0» l4» 14)
PRO
F <50 18 (COMMANDED «tP,Y)
PRO
06 i6 (Commanded r»p,y)
MONITOR AUTO MANEUVER
F 50 18 (COMMANDED R»P,y)
( Of 244/14, 14)
KEY ENTER
(99*35)
configure camera
CM/SEG/18/CEX-BRKT (RH wIn)
Mlf?(FU,250i INFINITY)6FPS»
15 MIN
<99*42)
<99*5] )
SUNUP
CMC WOOE-PrEE(AS RFQ for AGs
calib>
CMC MODE-AijTO (AFTER 3? SEC)
VERIFY max pB FOR AGS CAL 18
PERFORM systems CHECK AND
SWITCH VERIFICATION
WAIT FOR LM TO COMPUTE AGS
ALIGN AND give GO AHEAO* THEN
YAW 14 DEG left after
LM AGS calibration
(0,313/14,0)
(99*57)
MOVE TO LEB
a«rndz xpndr activation#*
AND SELF TEST
C« RNOZ XPNDR FLT BUSwCLOSE
rndz xpndr.*htR for (1 iMIK
SELF TEST)
RNpZ XPONOER PWR-ON
SYS TEST (LH)"XP0NDER
SYS TE^T(RH)-A(RRT xMTR OUT
PviR)
RNdZ XPNDR test-test (IHOLD)
SYS TEST IND-GREATER THAN 1 VD
SYS TEsT(RH)^B(RPT AGC .SI6)
RNoZ XPNDR test- test ((HOLD)
SYS TEST IND-GREATEr THAN 1
V0C
rndz XPNDR TEST-OPErAtE
SYS TEST IND-0-4.5 vDC'
SYS TEST(RH)-C(RRT FRBG LOCK)
SYs TEeT INO
•^LESS THAN ,8 VDC UNLOCKED
•'MORE THAN 4 VDC LOCKED
SYS TEST (RH)-e(RRT AGC SIG
OPERATE)
MOVE TO CMD SEAT
MISSION G DETAILED PROCEDURES
- 68 -
( 100 * 10 )
«*6DC align to
KEY V16NE0E
16 20 (R,P,Y)
fdaI sw2-inErttal
ATT SE'T thumbwheels TO N20
FDAI SELECT-1
null ATT ERROR NEEDLES
On FDAI I WITH ATT
SET thumbwheels
FDAI SELECT-1/2
ATT SET-GUC
DEPRESS >6UC ALIGN P8
ATT SET-IMU
FOAi SW2-0RB Rate
( 100 * 11 )
■■•♦OROEAL verification#*
KEY VB2E
F 04 12 {VEHICLE OPTION)
PRO
F 16 A4 (HA*HP*TFF)
CAlC AVE AuT
PRO“
ALT SET KNOB TO AVE ALT
KEY V83E
F 16 54 (R,R00Tt7hETA)
VERIFY RafiUOTsO
IF N0T»KEY V66E
SLEW/ADJUST FOAI TO THETA
PRO
(100*13)
S/C CONT-SCS
BMA6 MhDE(3)-ATTl/RATE2
##load dap**
KEY V48E
F 04 46 (Dap CONFIGURATION)
LOAD
11102
X lIIl
B
PRO
F 06 47 (CSM AND LM «T)
PRO
F 06 48 (SpS QMBL TRIM)
PRO
key V46E
•*PrOCEOURES FOR UNDOCKING**
install DOCKING TARGET
rate-high
ROT COvTR'pWR iDIRECT(BCTH)-
MNA/MNB
rhc-armed
THC-ARmFO
CB dock probe (2>-CLoSE>C
event tmr reset-down
EVENT tMR start (ON cDR SIGNAL)
MISSION G DETAILED PROCEDURES
-69-
-2S <100*15)
PROSE EXTO/REL-EXTD/REL (HOlh
UNTIL sep Puds 5 seconds
probe EXTU/REL T8(2) GrAy TO
8p to gray
MONITOR LM UNDOCKInG/MAINTAiN
Undocking attitude
(0»13/14»0)
PROBE EXTU/KEL^RETR
DV CG-CSM
AUTO RCS SELECT
-03(+YAW-X) -mNA
•C4(-PITCH-X)-MNA
ROT CONT PwR dir (BOTH)-OFF
CS dock prose (2) -open
MISSION G detailed PROCEDURES
-70-
« procedures for
a UNDOCKING T^IRU SEPARATION
e ««»* «««<♦«#*««■»** A *»««*«»*««■ o «<*■»#«■»»»»***««<»*•» *>
<»«cSM station keeping^*
ATT OB-MIK
RNOZ XPNDH PlwR-PWR verify
perform statiok keeping
MANEUVErS/MAINTAIN 40 FT
separation
(100+JRV
♦«acquire hga««
' KEY V64E
F Ob 5l [RH0»QAMMM, BLANK)
SLEW HI GAIN ANT
PRO -3
acouisitign of signal
ACQUIRE HGa
activate color tv
TAKE PHOTOS
INSPECT LN DURING LM 360 DEG
YAW
(100*32)
EMS FUNCTION-DV SET
SET DV INU To •►102,5
<100*34)
BMAG mode (3) -rate 2
S/C CONT-CMC
CMC MOOE-AUTO
MISSION G detailed PKOCEDURES
THC-LOCKED
RHC-LOCKEO
{ 1 0f)*35>
P30 kEy V37E30E
F 06 33 (GET Of SEP)
load get of separation
(100+39+58)
PRO
F 06 8i (VG-LV)
LOAD (0«0,-2,5)
PRO
F 06 42 (HA*HPfVG)
verify VGa2,5
PRO
F 16 45 (MKS,TFItMGA)
SET MDC ET TO TF If COUNTING
DOWN
CONFIRM MGA LESS THAN 4S DEG
PRO
F 37 BB
(100+37)
f»«RC5 SEPARATION BURN SETUP«<*
P41 KEY 41E
F BO 18 (Commanded r*p»y>
pRo
06 18 (Commanded r+p»y)
MONITOR ATT TRIM
F 50 latCOMMANOEO R*PfY)
rhc-armed
ALIGN i/C IN ROLL
PRO
06 i8 (Commanded r*p»y>
MONITOR ATT TRIM
F 50 18 (Commanded r»p,y)
^71-
key entep
06 as (VG-*800Y)
MONITOR COMP ACTV LT
BMaG mode (3) -ATT 1/RATE 2
rate-low
EMS FUNCTION-Oy
i00^40
MONITOR COMP ACTV lT-OUT
i00*3S
DSKY blanks
*00 + 30
16 85 (VG-BODY) (AVG g ON)
COMP acTv lt-2 sec flash
EMS mode-normal
• 00 + 25
CK VG FOR Hi PipA BIAS
(LESS IhAN ?,0 FPS per 5
SEC)
thc-ahmeo
)+00 (100*39*58)
F 16 S5 tVG-BODY)
SET MDC ET COUkTING UP
from separation
increase YG-bOOY PROM
(+2*5, (1,0) TO {*5. 0,0,0)
By thrusting aft
csM performs Separation burn
( 0,0t-2*5)
(O,90/U*0)
EMS MODE-STBY
record dv ind
EMS FlJNCTlON-OFF
hhc-lockeo
THC-LOCKEO
BMAG MnDE{3)-RATE2
AUTO R^S SEE A/C R0LU4)-0FF
PRO
F 37 BB
WHEN BURN complete, VCKE
Confirmation to lm
MISSION G detailed PROCEDURES
» PHOCEDURES FOH ' o
» separation thru TOUCHnnWN *
*«« 0 * «« <M» »*»«•»«» 0 4H» ««#■»«»«-» <MHt « «■« t» tf *
(100+44)
««maneuv£r to SxT Track attttud£<h*
KEY 20E
50 18 (COMMANDEU H,P,Y)
PRO
06 i8 (Commanded r*p,y>
MONITOR AUTO MANEUVER
50 i8 (Commanded k,p,y>
(Of l48/66f 0)
KEY ENTER
perform REinO? xponder checks
VHP ANT-RT
EMS FUNCTiON-VHF HNG
EMS MOOE-VHF RK(^
VHP A - CFF~
VMF 0 • DUPLEX
VHF RCV OMY-OFF
VHF RAN6ING-RNS
VHF RNG-RESET
monitor ENS FOR range
KEY V03E
F 16 54 (RfR DOTfThETA)
COMPARE EM$ ANp V03 RANGE
COMPARE LM RH RANGE AND
Range Rate with ems and
V83 range And range Rate
PRO
P20
F
F
MOVE TO LE8
perform OPTICS checks
zero optics-off
zero OPTICS-ZEroUS SEC)
zero optics-off
monitor lm In SCT ANO -SXT
OPTICS MODE-MAN
( 1 00+52 )
COPY DO! P76 PAD
COPY NO PDI 1+12 P76 PAD
COPY CSM RESCUE PAD
(100+54)
SUNDOWN
( 101 + 00 )
««realI6n imu to refsmmat««
adjust reticle brtness
P52 kEy V37E52E
F 04 06 (ALIGN OPTION CODE)
LOAD 00003 IN R2 FOR
realign to REFSMMAT
PRO
F 50 25 (OOOlBt PERFORM STAR ACfl)
OPTICS mode-manual
OHC-MANEUVER sct to aoc
T wo suitable stars
PRO
F 01 70 (Star code)
check first star code
zero OPTICS-ZERO(15SEC)
zero OPTICS-OFf
OPTICS MOOE-CMc
pRO
06 92 (SHAFTfTRUN, BLANK)
MISSION G detailed PROCFOURES
- 73 -
monitor CRT DRIVE TO star OnP
identify Star one
OPTICS MCOE-mAn
F -51 b6 (Please mark?
center FIRST STAR IN SVT
MARK ON STAR ONE
F -50 25 (00016* TERMINATE MARK SEQ)
PRO
F 01 71 (MARKED STaR CCOE)
PRO
F 01 70 (STAR CODE)
CHECK second star CODE
ZERO OPTICS-ZEPO (15SEC)
ZERO OPTICS-OFF
OPTICS MOUE-CMC
PRO
06 92 (SHAFT. TRUNtBLANK)
monitor opt drive to star Two
identify star two
optics mode-man
F 51 8b (PLEASE MARK)
center second star in sxt
MARK ON star two
F 50 25 (00016* TERMINATE MARK SEO)
pro
F 01 71 (MARKED STaR CODE)
PRO
F 06 05 (ANGLE DIFF)
COPY data on checklist
PRO
F 06 93 (GYRO TOpG AnOlFS)
COPY data on Checklist
move to cmd seat
CMC MODE-FREE
MISSION G detailed PROCEDURES
oRO
F 50 25 (OOOU* perform FINE ALIGN)
PRO
F 50 25 (00015*PEPFORM STAR AOG)
PRO
F 01 70 (STAR CODE)
LOAD third star CODE
CMC MODE-AUTO
MOVE TO LEB
zero optics-zero (15SEC)
zero OPTICS-OFf
optics MODE-CMc
PRO
06 92 CShAFT*TRUN*8LANK)
monitor optics drive t-c star
three
zero OnTICS-ZERO
POO KEY V37E00E
SET LEB ET COUNTING DoViN
TO LM DOI TigN
(101+38+48)
( 101 + 08 )
MOVE TO CMO seat
<*<»AlIGN GDC to IMU*4
key V16N20E
16 2 o (R*P.Y)
FDAI SW2-INERTIAL
ATT SET thumbwheels TO N20
FDaI SELECT-1
- 74 -
NULL. ATT £HH0R nEEDLLS
On foai 1 w»rTH att
Set thumbwheels
FDA l SELECT-1/2
ATT SET-GOC
DEPRESS 6UC align Pfi
ATT SET-IHU
FDAl SW2.*0RB RatE
•»»0RDEAL VERlFlCATrON«<>
key VB3E
F 16 54 (R,ROOTtTHETA)
SLEW/AOJUST FOAI TO TheTA
PRO
(lOUlO)
««MCC-ri uplink (CSm and IM vECT0R)«**
0 + 00
UP TLM(Cv) (MOC) -accept
MONITOR UPLINK ACT LT-ON
MONITOR GNU IjPlTNK
MONITOR UPLInK act LT«0FF
UP tlmicm) (moc) -block
confirm COmP act LT-OFF
SET MDC ET counting DOWN
To LM OOl TTGN
(101*30)
(101+31)
LOSS OF SIGINAL
VHF am A-SIMpLEX
VHF AM B-OFP
VHF RCV CNLY-ri nATA
TAPE RCDP FWO-FWO
pcm hit rate-Low
(101+3J)
<m»maneuv£r to sxt Track attitude***
P?0
KEy V37E20E
F .50 18 (Commanded r^PiY)
PRO
06 18 (Commanded R.P 9 Y)
MOVE TO LEB DURING AUTC
manfuver
F 50 18 (Commanded r»p»y)
< 0 , 217/332', 0)
KEY ENTER
ZERO OPTICS-OFF
OPTICS MODE-CMC
(101+30+48)
««***«»***«**»«
LM 001 burn
(-72,7,0,14,5)
MOVE TO CMO seat
CONFIRM LM DOI BURN COMPLETE
(101+40)
SUNUP
(101+42)
VHF
VHP
VHF
VHP
AM A-OFF
AM B-DUPLEX
RCV ONLY-OFF
ranging-rng
MISSION! G detailed PHOCfnURES
-75-
VHF RAN(3I\G-HESET (NO VOICE 1?
SEC)
COMPUTE ROOT PPOV VHf RANGE
P?6 KEY V37E7bE
F 06 84 (OV»S OF Lm DOt BURN)
Load (-72*7, o,U. 5)
PRO
F 06 33 (GETI of UOl)
load lm OOI TIgn + 2o SEC
(101+39+08)
PRO
F 37 B8
KEY V82E
F 04 06 (VEHICLE OPTION CODES)
LOAD R2=6ooO?
PRO
F 16 44 (HA»HP,TFF)
VERIFY (60X9}
PRO
F 37 0B
noi+44)
«*mA(\JEUVER to track ATTITU0E*«
P20 KEY 2PE
MOvE TO LEB
(101*49)
ZERO OPTICS-ZEROCIS SF.C)
ZERO optics-off
staRt cameras remote operation
initiate lm optics Track
MISSION G detailed PROCEDURES
(101*52)
SET LEB ET counting DOWN
To LM PDI TIGN
KEY V93E
key V57E
F 51 Be (PLEASf MARK)
KEY V87E
optics mode manual
OHC-CENTER LM IN SXT
take 15 MARKS IN NEXT
Fifteen minutes
pro/process last mark
(102*07)
cease tracking
zero optics-zero
optics mode-cmc
move to cmd seat
(102*17)
ACQUISITION OF signal
POO key V37E00E
key V64E
F 06 5l (RHOtGAMKA*BLA'NK)
slew hi gain Ant
PRO
(102+19)
««MaNEUVER to track attitude**
P20 key V37E20E
F 50 la (Commanded PtP»Y)
PRO
06 18 (Commanded r»p*y)
move to LEB DURING AUTC
Trim
,F.SO 18 (CoMMANOEQ RfP,v)
(0»35E/330iO)
aoa^as)
<i02«aa)
POO
KEY ENTER
ZERO optics-off
initiate track only
obtain GC/NO Go for pot abort
key V37E00E
KEY V48E ^
F 04 46 (Dap CONFIGURATION)
LOAD
llldi
PRO
F 06 47 (CSM and LM WT)
PRO
F 06 48' (SPS 6MBL TRIP)
PRO
KEY V49E
F 06 22 (COMNANOED R*P,y»
LOAD (0tl40»0)
PRO
F SO 18 (CdMMANDEiJ «*P<Y)
OPTICS Mobe-MANUAL
OHC-CENTER Lw in sxt .
a02«35^l4)
LM ,P,0’i^ ' ■ .
< 102 * 36 )
PRO
06 18 (Commanded r*p,y)
MISSION e detailed procedures
(PITCH DOWN ,2 DEG/SEC TO
P52 ATT)
a02*46)
M$FN ENABLES S-BAND RELAY
(102+47411)
lm Touchdown
(102+53)
!(i0a+55)
(102*57)
-77-
• tt
• Procedures for touchdown *
» TO csM plane Change »
• ... ^
»»««*«#«••»«««««««
(103^01)
’««REALIGN IMU to HEFSMMATftfr
'T
PS2
ADJUST reticle BRTnESS
KEY V37E52E
F OA 06 {ALIGN OPTION CODE)'
load 00003 IN P2 FOR
REALIGN TO REFSMMAT
PRO
F -50 25 {OOOIS* PERFORn STaR ACO)
ZERO optics-off
OPTICS MOUE-MAN
OHC-NANEUVER sct to acq
TWO SUITABLE STARS
PRO
F 01 70 (STAR CODE)
check first star code
OPTICS MOUE-CMC
PRO
06 92 (ShAFT»TRUN*BLANK)
MONITOR OPT DRIVE TO STAR ONE
IDENTIFY Star one
OPTICS mcoe-man
F .51 Bfi (PlEASE MARK)
cENtER First star in sxt
MARK ON star ONE
F .50 25 (oToTfet terminate mark Seq)
PRO
F'oi 71 (Marked star codE)
PRO '
F 01 70 (STAR CODE)
check SECOND Star code
ZERO OPTICS-ZERO UBSEC)
ZERO OPTICS-OFF
OPTICS MODE-CMC
PRO
06 92 < shaft *TRUN^BLANK)
monitor -opt drive to star two
■ identify star two
OPTICS MODE-MAN
f .51 bb (Please mark)
center second !star in .Sxt
MARK ON STAR TWO
F 50 25 (000l6f TERMINATE MARK SEQ)
PRO
F 01 71 (MARKED STAR CODE)
PRO
F 06 05 (Angle diff)
COPY DATA -ON CHECKLIST
PRO
F 06 93 (GYRO TORQ ANGLES)
COPY DATA ON CHECKLIST
MOVE TO CMO seat
CMC MOnE-FREE
PRO
F .50 25 ( 00014 f PERFORM FI-NE ALIGN)
PRO
F .50 25 (OOOIS. PERFORM STAR AQC)
PRO
F 01 7o (STAR CODE)
load third star CODE
CMC MOOE-AUTO
MOVE TO LEB
MISSION 6 detailed PROCEDURES
-78-
ZERO optics-zero (15SEC)
ZERO OPTICS-OFf
OPTICS MCCE-CMc
' PRO ■
06 92 (SHAFT*TPUNt9LANK)
MONITOR OPTICS DRIVE TO STAR
Three
ZERO optics-zero
POO KEY V37E OOfc
(I034-07)
move to cmd seat
<H»ALIGN SDC TO IMU<»tt
KEY V16N20E
16 20 (R»P*Y)
FDAl SW2-INERTTAL
ATT SET THUM8«(HEELS TO N20
FDAl select-1
null att error meedles
On FOAi 1 with ATT
SET thumbwheels
FDA l select-1/?
ATT SET-6DC
DEPRESS GUC ALTON PB
ATT SET-INU
FDAl SW2-0R8 Rate
<103+09)
♦^ORDEAL verification**^
KEY V83E
F 16 5<v (RtROOT»THETA)
slew/aojust foai to theta
PRO
{103*17)
COPY P22 PAD AT GET lOA+25
\(l03+29)
^ LOSS OF signal
(103*39)
SUNUP
(104+01)
SC CONT - SCS
MNVR *X To 2 DEG BELOW HORIZON
key V48E
F 04 06 (Dap CONFIGURATION)
load
11100
01111
PRO
F 06 47 (CSM and LM WT)
PRO
F 06 40 (SPS GMBL TRIM)
PRO
KEY V49E
F 06 22 (Commanded r,p,y)
LOAD (0»330»0)
PRO
F 50 18 (Commanded r#p.y>
BMAG mode (3)-RATE 2
sc CONTflOL-CMC
(104*07)
PRO
06 18 (Commanded r.p*y)
aFter maneuver started
man att (PITCH) -accel :cmd
move to leb
MISSION G detailed PROCEDURES
‘<H»0RBIT navigation program
P22 KEY V37E22E
F OG 45 (BLANK. BLANK, mgA )
PRO
F 05 70 (BLANK, LMK CODE, BLANK)
KEY V22E10000E
F 06 89 (LAT# L0NG/2t AlT)
load (MK COOROS)
OPTICS zero-off
PRO
06 92 (SHAFT, TRUN>
OPTICS mode-manual
F '51 88 PLEASE MARK
take 5 MARKS 30 SEC APART
PRO
F 05 71 (BLANK, LMK CODE, BLANK)
PRO
F 06 89 (LAT,L0NG/2,ALT)
PRO
F 06 49 (DELTA R, DELTA v, BLANK)
hold for 30 SEC
PRO
F 06 89 (LAT, LONG/2, ALT)
KEY V34E
F 37 88
POO KEY OOE
T104+I5)
‘AOs
key V46E
manual ATT PITCH-RATE CKO
KEY V48E
F 04 06 (DAP CONFIGURATION)
load
11101
oiin
F 06 47
F 06 48
F 06 22
F .50 18
06 18
F 50 18
( 104*S1)
(104+55)
F 06 51
(104+57)
(104+59)
PRO
(CSM AND LM WT)
PRO
(SPS GMBL TRIM)
PRO
KEy V49E
(Commanded r,p,y)
LOAD (270,101+45)
(Commanded r,p',y)
BMAG mode (3)-RATE 2
sc control-cmc
PRO
(Commanded r,p,y)
mOnitor auto maneuver
(Commanded r»p»y)
(270,101,45)
key enter
sundown
key V64E
(Rho, Gamma, BLANK)
slew HtGH gain ant.
PRO
ACQUIRE HGA
FOAI 2-INERTIAl
««McC-H uplink (PLANE CHANGE**
HEFSMMAT)
UP TLM(CM) (MOC)-ACCEPT
monitor uplink act lt-^on
monitor 6N0 uplink
monitor uplink act lt-cff
MISSION G detailed procedures
-SO-
UP TLM<Cf/) (MOC) -riLOCK
( 105*04)
C^C N>ODE -FREE
«»REALieN IMU TO PLANE CHANGE
refsmmat»oyho T0RQUING*<»
PS2 KEY V37E52E
F 04 n6 (OO.O0i*OOOO2»8LANK),
,PRO
F 6^ 22 (R,P»Y) ‘ ‘
load N22 .
PRO
F '50 25 (00013 GyRO T0R(3UE)
key enter
16 20 (R,P,Y) ,
WHEN TORQOE COfpLETE
F 50 25 (00014 ALIGNMENT CHECK)
KEY ENTER .
F 37 98
(105*08)
POO KEY OOE
CMC MODE-HOLO
(105*11)
<H4ALI6N goc tc imu*h»
KEY V16N20E
16 20 (H,P,Y)
' FDAI SW2-In£RTIAL
ATT SET thumbwheels TO N20
FDAl SELECT-1
null ATT ERROR nEEoLES
ON FDAI 1 WITH ATT
SET thumbwhfels
FDAI SELECT-l/?
ATT SET-6UC
depress -GDC align PB
MISSION 6 detailed PROCEDURES
att SET-IMU
(105*12)
(105*27)
(105*37)
(106*13)
(106*15)
initiate eat Period
LOSS of signal
SUNUP ' ‘
acquisition of signal
KEY V64E
F 06 51 (RH0,QAMMA»BLAN'K)
SET ANTENNA TO THESE ANGLES
PRO
ACQUIRE HGA
UPLINK CSM STATE VECTOR#*
anD plane change target load
UP TLM'(CM) (MDC) -ACCEPT
MONITOR' UPLINK ACT LT--ON
monitor GNO UPL'I^^K
MONITOR UPLINK ACT LT-CFF
UP TLM (CM) (MDC) -BLOCK
RECORD MNVR PAD
(106+37)
key V49E
F 06 22 (Commanded RfP»Y>
LOAD (0,0»0)
PRO
F 50 i8 (Commanded r*p*y)
bRag mode (3) -bate 2
sc CONTROL-CMC
CMC MflDE-AUTO
■ PRO
- 81 -
06
16
(COMMANDED
R»p,y)
monitor auto maneuver
F SO
18
(COMMANDED
RfP,Y)
( 0 , 0 * 0 )
KEY enter
OPTICS MOOE -Cwc
ZERO OPTICS - OFF
KEY V41E N91E
F 21 92 SHAFT, TRUN
LOAD N92 WITH PAD SHAFT AND
TRUNION
41 OPTICS DRIVE
(1Q64>50)
sundown
OPTICS MOOE-MAMjAL
Verify star in sxt field
Of view
ZERO OPTICS - ZERO
OPTICS NCDE-CMC
(106*52)
P30 key V37E30E
F 06 33 (GETI of CSM PlaNE CHANGE)
load get of PLfiNE change
(107+05+34)
PRO
F 06 91 (VG - LV)
LOAD pad Plane change dv
PRO
F 06 42 (HA*HP,V6)
verify vgs Pad dvr
PRO
F 16 45 (MKS,TFlfMGA)
' SET MDC ET To TFl«COUNTlNG
Down
confirm MGA less than 45 DEG
PRO
F 37 Be
(106+56)
P40 key 40E
F 50 18 (Commanded r,p,y)
pfto
06 18 (Commanded r*p,y)
MONITOR ATTITUDE TRIM
F 50 18 (Commanded r*p,y)
( 106+57)
■<MtSETUP SPS plane CHANeE»«
MN Bus TIE (2)-ON('UP)
SPS HE VLV TB (BOTH)^BF
SPS HE VLV (BOTH)-AUTO
nOnEsS bus-mna
RHC-ARMEO
BMAG MnOE(3)-ATTl/RATE2
perform mtvc check
TVC SERVO PWR UACI/MNA
TVC SERVO PWR 2-AC2/MN8
TRANS CONTR PWR- ON
RHC PWR NORM 2-AC
GMBL MtRS pitch 1 STRT-ON
GMBL MTRS yaw 1 STRT-ON
TMC-CLOCKWISE .
RMC-VERIFY NO JMTVC
GMBL MTRS PITCH 2 STRT-ON
GMBL MTRS YAW 2 STRT-ON
SET SpS gimbals TW(2)-TRIM
rhc-verify mtvc
THc-NEUTRAL
RHC PWp NORM 2-AC/OC
MISSION G detailed PROCEDURES
-82
«>2«00
«»00'fr35
<*00430
«004l5
"OO^OS
RHC-LOCKEU
' PRO
06 18 (COMMANDEtJ R»P,Y)
MONITOR ATT TRIM
F 50 18 (COMMANDEO H«PtV)
KEY enter
F 50 25 (00204*GmBl DRIVE TEST)
RHC PWR DJRECT{ROTH)-MNA/MNr
' RATE-HlXaH
AUTO RCS SEE A/C R0LL(4)-«NA
• PRO ' ^
‘MONITOR GMBL DRIVE
SEQ AM) trim
06 40 (TFI 9 VG 9 DVM) *00+
FOAl SCAlE- 5,/5
VERIFY SpS TH lT-OFF
EMS MOOE-STHY
EMS FUNCTION-DV SET
LOAD plane change DV
EMS FUNCTiON-DV
THC”ARMED
DV Thrust (BOTH) -NORMAL
dskY blanks ‘
06 40 (TFI,V 6 »DVM)
EMS mode-normal
CK UVM For hi pipa eiAS
<LESS THAN ? FPS/5 SEC)
> +
perform L’t-LAGE
F 99 40 ' (REQUEST FOR ENGINE ENABLE)
PRO
06 40 (TFI,VG,DVM>
(107 + 05.*34)
cSm performs Plane ch/dnge
Burn
monitor
SPS THRUST LT-ON
ov indicator-decreasing
UULAGE-cFF
06 40 (TFC,Vp,DVM)
monitor SPS OPERATION
PC INDICAT0R-95-10B PSI
mOnItoRsps engine cutcff
SPS thrust LT-OFF
F 16 40 (TFC»VG,DVM)
DV THRUST (BOTH) -OFF
MONlTOg
Pc tNDICATORoO
SPS INJ VLV IND(4)-CU0SE
SPS HE VLV TB<B0TH)-BP
SPS GMBLS return TO SERVO
NULL
GMbL MtRS-OFF (SEQUENTIALLY)
TVC SERVO PWR (BOTH) -Off
FOA l SCALE-S/1
rate-low
ROT CONT PWR DIRECT {B0TH)‘-0FF
PRO ‘ . .
F 16 85 (VG-BOOY)
thc-null V6 components
MISSION G' detailed PROCEOURES
-83-
AUTO RCS SEt, fl/C R0LLt4)-0FF
thc-lockeo
RriC-LOCKEU
bmag hooe ( 3) ^RatES
PRO
F 37 Bti
POO key OOE
(107+08)
KEY V64E
F 06 51 (RhO GAMf^A, blank)
SET antenna to these anGles
PRO
ACQUIRE H6A
uplink liftoff REFSMMat**
UP tlm(Of) (mdc) -accept
MONITOR UPLINK ACT LT-ON
monitor gno uplink
MONITOR UPLINK ACT LT-OFF
UP TLm<Cm) (MOC)-BLOCK
(107+10)
KEY \/49E
F 06 ZZ (COMMANDEU R*P,Y)
LOAD (0»A5*0)
PRO
F 50 10 (COMMANDED K,P,y)
BMaG M00E(3)-flATE 2
PRO
06 i8 (Commanded Rfp,Y)
after mnvh Complete
CMC mode - Free
(107+14)
<»«REaLIQN IMU to landing site
REFSMMAT tGYRO TORQUlNG<»<»
P52 KEY V37E52E
F 04 06 (000O1,00001«BlANK)
PRO
F 06 22 (R,P,Y)
load N22
PRO
F .50 25 (00013 GYRO TORQUE)
KEY ENTER
16 2o (R,P*Y)
when TORQUE COMPLETE
F 50 25 (00014 ALIGNMENT CHECK)
key enter
F 37 BB
(107+17)
POO KEY OOE
CMc MODE « HOLD
(107+18)
««AlIGN GDC TO IMU**
kEy V16N20E
16 20 lR»PtY)
ATT SET thumbwheels TO N20
FOAI $ELECT-1
null ATT ERROR NEEDLES
ON FOA! 1 WiTH"aTT
SET thumbwheels
FOAI SELECT-1/2
ATT SET"6DC
depress GDC ALIGN PB
ATT SEf-IMU
fDai sui2»oRB Rate
(107+19)
**0RDEaL verification**
key V83E
F 16 54 (RfRDOTtTHETA)
slew/adjust FDai to theta
mission G DET'AIlEC procedures
-84-
PRO
a07^25)
LOSS OF signal
(107*26)
mnvr to attituof for rest
PERIOD
key V49E
F 06 22 (COMMANOEO R,P,Y)
load' (135»97/19p,0)
PRO'
F 50 la {COMMANDED R«PtY)
’ BMA6 mode (J)-RATE 2
SC contrcl-cmc
CMC MODE-AUTO
PRO
06 IH (COMMANDED R«P»Y)
MONITOR AUTO MANEUVER
F 50 iH {Commanded r,p,y)
(82,128/218,0)
h;ey enter
(107*35)
BEGIN REST AnO EAT PERIOD
MISSION G detailed PHOCEOURES
-85
* ^
« PROCEDURES Thru »
insertion' •»
d »
Q24+QQ )
POO KEY V37E00E
KEY V64E'
F 06 61 (RHO GAM^^A♦BLA^K)
SLEW HI GAIN Ant
PRO
0 24+02),
' ■■ KEY V40E
F 04 46 (DAP CONFIGURATION)
load
lllOl
Ollll
PRO
F 06 47 <CSM and LM WT)
PRO
F 06 40 (SpS 6MBL TRII^)
PRO
024+03)
key V49E
F 06 22 (Commanded r»p,y)
LOAD (0i206»0)
PRO
F 50 18 (Commanded k»p,y)
BMAG mode (3) -rate 2
sc comtrol-cmc
CMC MODE-AuTO
PRO
06 ]8 (COMMANDED H»P,y)
MISSION G detailed PROCEDURES
monitor auto maneuver
F 50 18 (Commanded r*p*y)
(0.206,0)
KEY enter
(124+15)
KEY V49E
F 06 22 (Commanded r,p,y)
load (0,73»0)
PRO
F -50 10 (Commanded r,p,y)
MOVE TO LEB
2£R0 OpTICS-ZEROdS -SEC)
ZERO OpTICS-OFp
OPTICS mode-manual
OHC-CENTER LH IN SXT
(124+23+25)
PRO
06 10 (COMMANDED R*P,Y>
<PIHH down at 2 DB6/SEC
TO P52 ATT)
(124+23+25>
«•» 4 « 4
LM LIFT-OFF
(124+30+39)
LM completes Insertion rurn
confirm LM BURN COMPLETE
(124+34)
F SO 18 (Commanded r,p,y)
(0,202/73*0)
KEY ENTEP
ZERO OPTiCS-ZEPn
OPTICS MCUE-CPC
key V48E
F 04 46 (DAP COMFIGOPATION)
LOAD
11102
X’llH
PRO ' ’
F 06 47 (CSM and /if)
PRO
F 06 48 (SP^ GmBl TRIP)
PRO
MISSION G OF.TatlED PHOCEnURES
-87-
*« -tHf ^ ^ ^ y ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^
* procedures for h
* iNStHTlON Thru CST tt
<H> ## 1H» ««*«##*« tt ■» fl. *H» fl. ^ ## ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^ ^
F 50 25 {00016* TERMIN/JTE MARK SEO)
PRO
F 01 71 (Marked star oodE)
PRO
(124+35)
sundown
SET LEB ET counting DOWN TO
CSl' USiNS LM CSl tksn
AND MISSION timer
<H»r£ALIGN IMU To REFSMMAT«tt
P52 key V37E52E
ADJUST reticle BRTNESS
F 04 Ob (ALIGN OPfl&N CODE)
load 00003 IN 92 FOR
Realign to refsmmat
PRO
F 50 25 {00015* PERFORm STAR ACQ)
OPTICS MCOE-MamjAL
OHC-MANEL'YER 5CT To ACQ
Two SUITABLE STARS
PRO
F 01 70 (STAR CODE)
check FIRST STAR CODE
ZERO optics-off
OPTICS MCUE-CMC
PRO
06 92 (SHAFT*TRUN*BLawK)
MONITOR OPT DRIVE TO STAR ONE
IDENTIFY STAR CK'F
OPTICS mode-man
F 51 rb (Please mark)
center First star in sxT
MARK ON SIaR One
F 01 70 (STAR CODE)
CHECK second STAR CODE
HERO OPTICS-ZERO (IBSEC)
ZERO OPTICS-OFf
OPTICS MODE-CMc
PRO
06 92 (ShAFT*TRUN*0LANK)
monitor opt drive to star TI»)0
identify star two
OPTICS mode-nan
F 51 0B (PLEASE MARK)
center second .star in .sxt
MARK ON STAR TWO
F 50 25 (00016* TERMINATE MARK SE(3)
pRO
F 01 7l (MARKED STAR CODE)
PRO
F 06 05 (ANGLE DIFF)
COPY DATA ON CHECKLIST
PRO
F 06 93 (Gyro torq angles)
COPY oXTA on OHECKLIST
MOVE TO CMD SEAT
CMC MODE-FREE
PRO
F 50 25 (00014* PERFORM FINE ALIGN)
PRO
F 50 25 (00015*PERFORM STAR AQ(J)
PRO
mission g detailed procedures
- 88 -
F 01 70 (STAR C00£)
‘load third star code
CMC MODE-AUTO
move to LE8
ZERO QPTICS-ZERO (15SFC)
ZERO optics-off
OPTICS WCUE-CMC
PRO
06 92 (SHAFT*TRUNtHUaMK)
■ monitor optics drive TO star
tHREE
ZERO optics-zero
(124*40)
POO KEY V37E00E
key V64E'
F 06 5l (RhO GAMMA.fbLANK)
SLEW HI GAIN Ant
PRO
state vector uplink^^*
UP TLM(CM) (MDC)-ACCEPT
MONITOR UPLINK flCT LT-ON
monitor gno uplink
MONITOR UPLINK ACT LT-OFF
UP TLM (CM) (MOC) -BLOCK
( 124*44)
»<»MANEUVEr to track attitude^*
P^O KEY V37E20E
F 50 la {COMMANDED R»P,Y)
PRO
06 iB (COMMANDED R»P»Y)
monitor AUTO Trim
F 50 i8 (Commanded r^p^y)
(0, 232/73* 0)
KEY ENTER
EMS FUNCTION-VHF RNG
EMS MOnE-VHF RNG
VMf RNg-RESET
(124+47)
P32
F 06
F 06
F 06
F 16
(l24<-49)
F r51
KtY V37E32E
11 (GETI‘-CSI)
LOAD LM'CSI tiGN
( 12 ^* 21 * 20 )
PRO
55 (N,E,CENTANG)
verify Rla*00001
LOAD R23+208.30
LOAD R3s+130,Oo
PRO
37 ((SETI-TPI)
load Lw TPI TIGN
(129*58i27)
pRo
45 (MKS»TFI-CSI»-00001>
SET LEB EtaTFl
kEy V32E
KEY V93E/REINITIALIZE % MATRIX
key V57E
Be (PLEaSf MARK)
KEY VR7E (VHF RANGING)
ZERO optics-off
OPTICS MOOE-MAN
OHC-CENTER LM IN SXT
take 5 MARKS I'fv NEXT 5
MINUTES
PRO/PRnCESS LAST MARK
MISSION G detailed PROCEDURES
-89-
F 16 45 (MKS,TFl-CSl»-n0001)
ZERO OPTICS^ZERO
OPTICS MCOE-CMC
KEY V93E
take 5 marks In 5 MINUTES
move to command seat
• 1
(124*59)
KEY V88E
key V90E
F 04 l2 {VEHICLE OPTION)
load R2=00002
PRO
F 06 16 (TIME OF EVENT)
load LM CSI TIGN
(125 + 2U20)
PRO
F 06 90 {Y*YD0TiP5D
VOICE lm ydot to LM
PRO
F 16 45 (MKS,TFl-CSIf-00001 )
key V90E -8
F 04 12 (VEHICLE OPHOn)
load
RSsiOOoOl
PRO
F 06 16 (TIME OF EVENT)
load CSM CSI tign
(125*21*20)
PRO
F 06 90 (Y,YD0T*PSI) ,6
COPY (-)CSM ydot
MISSION G detailed PROCEDURES
ON CHECKLIST
PRO
F 16 45 (MKSiTFI-CSI»-OOOOl)
key V87E
take 8 MARKS I'N 8 MINUTES
(125+08)
LOSS OF signal
l(l25*Q9i t
pro/make final pass
F 06 75 (DH»DT-CSI/CDH,0T-CDH/TPI>
COPY DATA ON QHECKLIST
PRO
F 06 8l (CSI VG--LV)
OVER WRITE N81 WITH
(-) CSM YDOT
COPY data on checklist
pRO
F 06 82 (COH VQ-LV)
COPY DATA .ON CHECKLIST
PRO
F 16 45 (MKS»TFI-CSI »MgA)
set MD? ETaTFl
PRO
F 37 BB
(125*13)
P40 KEY 40E
F 50 18 (Commanded r.p,y)
KEY V56E
PRO
06 18 (Commanded r*p*y)
monitor maneuver
F 50 18 (Commanded r*p»y)
(Ot 156/269, 0)
(125+15)
COPY lm CSI PAC (P76)
- 90 -
*«SETUP SPS CSI tJACKUP**
EMS yODE-STBY
EMS FUNCT10>^-0 v set
LOAO CSI BURN vr
EMS FUNCTION-Ov
FDAI SCAlE-5/5
rat£-hiqh
fiHC PWR OlR£Ct <R0TH) -MNA/MN0
BMAG M0DE(3)-ATT 1/RATE 2
JVC GMBL URIVE iROTH) -AUTO
AUTO RCS SeL A/c ROLL (4)-MNA
rhc-armec
-2
06 40
-0043s
.
-00430
06 40
-00405
F 99 4o
0400
(125421420)
key enter
(TFI«VC»DV)
ov thrust A-nORMAL
THC-ARNED
osky blanks
(Tfi,vg*dv) {ave e on>
EMS MOOE-NORMAl
<TFI»VG,0V)
.3
align s/C to 0 DEG ROLL
PRO
06 la (COMMANDED R»P,Y)
MONITOR ATT TRIM
f 50 i8 (Commanded r,p,y)
«*GDC ALIGN*H»
ATT SET thumbwheels TO N18
FDAl SELECT-1
null ATT ERROR nEEOLES
ON FOAI 1 WITH ATT
SET thumbwheels
FOA l SELECT-1/2
ATT SET-GOC
gdc align pb-push
ATT SET-IMU
KEY enter
F 50 25 (00204, GMBL DRIVE TEST)
UM CSI BURN
(49.4,0,0)
* 4MH( «Hj -H. <»*»»#«*■»**■»** <HH» « - tt ««•■»■»■»■»»«■»*«*« e »**«•««« HH**
« IF lm Cannot perform the burn *
* MN BUS TIE (2)^0N<UP> *
» NONESS BUS-MNA »
« SPS HE VLV T8 (BOTH1-0F «
» SPS HE VLV (BOTH)-AUTO «
VERIFY SPS TH LT-OFF
4 «
<t-00*15 THC-APPLY ullage »
4 GMBL MTRS(4)-0n (SE(3UENTIALLY)*
« • TVC SERVO PWR 1-ACI/MNA 4
« TVC SEpVO PWR 2-AC2/MNB *
4 pRO 4
4 «
4 4flr4<»44444tt4’444*44'44«4««44»*4* 4
MISSION G detailed PROCEDURES
«
»
»*00*0l
tt
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
ft
CSM BACKUP CSI BURiM ft
(-49._9,0,6)
(oae 6 / 26 Q»o)
ft
ft
06 40 (TFC,V6»OV) ft
THC-TERMIJNATE ullage *
MONITOR SPS BURN «
F 16 40 (TFC,VG»DV) «
DV Thrust a-off ft
RMfiL MTRS (4 )-*OFF/SEQUFNTIaLLY*
PRO ft
F 16 fi5 (VG-0OOY) ft
THC-NULL VGS ft
THC-LOCKEU ft
TVC SERVO PWR (boTH)-OFF *
EMS MOOE-STBY ft
SPS RE Vlv (BOTH)-OFF *
MN BUS TIE (BOTH) -OFF *
NONESS tiUS-OFF ft
PRO
F 37 RH ft
(Continue oEtahed PRncEnuRFSft
HUT DELETE P?6) ft
ftftftftftftftftftftftft ftftft ft «« ft^-JHtft<t<H»ft«
confirm LM burn complete
P76 key V37E76E
F 06 R4 (OV»S OF CSI BURN)
rhc-locked
THC LOCKED
AUTO RCS SEL* A/C ROLL (4)-0FF
EMS FUNCTlON-Vwp RimG
EMS MOOE-VHF Rng
MISSION G detailed PROCEDURES
VHF RNG-RFSET
FOaI SCALE-5/1
RATE-LnW
HOT cont PWR Direct (scth)-off
BMaG mode (g) -rate 2
TVC CIMBAL drive (B0TH) -»1
P76 KtY V37E76E
F 06 84 (bVfS OF LM CSj BURN)
load (50*1»0,0.1)
PRO
F 06 33 (OETI of CSI)
load Lm CSI TlCN ♦ 23 *SEC
(125421+43)
PRO
F 37 B0
key V82E
F 04 06 (Vehicle option codes)
load R2s00002
PRO
F 16 44 (HAfHPftFF)
verify (45X45)
PRO
F 37 BB
(125+22)
SUNUP
-92-
» - PROCEDURES POH ^
* csi Thru cdh **
(125*27)
»«MANEUVER to track ATTlTUnE««
P20 KEY POE < ‘ ’
F 50 18 (CoMRANOeO RfP,Y)
PRO
06 J8 (COMMANDED R»P,Y)
MOVE TO LEB DURING
AUTO maneuver
F 50 18 (COMMANDED f<»P,‘Y)
(0f2P8/p99t0)
key enter
SET LEB ET COUNTING DOWN TO
CDH USING lM cdh TIGN
AND MISSION timer
zero OPTICS-OFF
-51 (125+29)
KEY V57£
f 51 BH (PLEASE MARK)
’ KEY VB7E
OPTICS MOOE-M'AN
OHC-CENTEH LM IN SXT
make 3 MARKS IN NExT
3 minutes
(125*32)
PRO/PROCESS LAST MARK
KEY V67E
MISSION G detailed PROCEDURES
F 06 99 (POS ERR,V£L ERR*OPTION CODE)
load Wn
(*0?000,*00020f0000l)
PRO
k£Y V57E
F .51 bb (Please mark)
make 11 MARKS IN NEXT
11 minutes
(125+43)
PRO/PROCESS LAST MARK
OPfli'S mode-cmc
COPY LM pc TljSN
KEY V88E
key V90E
F 04 12 (VEHICLE OPTI.ON)
load r2=00002 '' '
PRO
F 06 16 (TIME OF EVENT)
load LM' PC TIQK
(125*50*40)
PRO
F 06 90 (Y» YOOTi PSD
VOICE LM YDOT to LM
PRO
COPY LM PC PAD
(125+45)
KEY V57E
F 51 B0 (Please mark) '
key V87E
OPTICS mode-man
OHc-CENT'ER LM' in SXT
-93"
make s marks in next
5 minutes
PRO/PROCESS LAST MaRk
OPTICS MCOE-CMC
{\2B*50)
P76 KEY V37E76E
r 06 04 (DV»S OF UM PC BURN)
LOAD LM plane change DV ♦ S
PRO
F 06 33 (GeTI of PC BURN)
load geti-pc burn
(l?5+50^40)
29 a25+50+40)
LM PLANE change
confirm lm pc burn
PRO/INCORPoRATE P76
F 37 BB
2? (125+53)
P20 KEY20E
key V57E
F 51 as (Please marK)
KEY V07E (VMF RANGING)
OPTICS MCOE-MAN
ohc-center LM in SXT
take 4 marks IK next
3 minutes
(125*54)
AC(JUISITI0N OF signal
24 (125*56)
KEY V93E (REINITIALIZE W MAT)
take ft marks Ik next
9 minutes
PRO / PROCESS LAST MARK
zero OPTICS-ZEPO
OPTICS mooe-cmc
-15 (126+05)
KEY V08E
KEY V90E
F 04 12 (VEHICLE OPTION)
LOAD R2a00002
PRO
F 06 16 (Time of event)
obtain LM COH tiGN
LOAD LM CDH TIGN
(126*19*40)
PRO
F 06 90 (Y,Y00TiPSI)
VOICE i M YDOT TO LM
PRO
MOVE TO CMD seat
KEY V9«E
F 04 12 (VEHICLE OPTION)
LOAD R2=00001
PRO
F 06 16 (TIME OF EVENT)
load CSM CDH TiGN
(I2ft*l9*40)
PRO
F 06 9o (Y,YD0 TiPSI)
COPY (-) CSM YCOT
ON CHECKLIST
PRO
-10 (126*10)
P33 KEYV37E33E
F 06 13 (GETI-CDH)
MISSION G detailed PROCEDURES
-94-
F 16 4S
F 06 75
F 06 81
F 16 45
F 37 BB
|( 126 + 14)1
P4i
F 50 xe
load LM CUH TlGt\J
‘ (l26 + iy+'40>
PRO
(MKS,TFl-CDH,-n 0001 )
PRO/MAKE final PASS
(OH»OT-COH/TPI*r)T-TPI/TPl)
COPY DATA ON CHfCKLlST
PRO
(COH VG-LV)
over write N 81 with
(-) CS« YDOT
COPY data on Checklist
PRO
(MKS,TFI-C0H,M6A)
SET MDC ETaTFI
PRO
KEY 41E
(COMhANOEO HtP,Y)
KEY v'iefe;
key enter (bypass MNVR)
06 85 (VG-800Y)
ON FOAI 1 with ATT
SET thumbwheels
FOA l SELECT-1/2
ATT SET-GDC
depress 6 DC align PB
aTt SET-IMU
kEy release
( 126 + 16 )
COPY LM COH P7.6 PAD
~00+35
qsky blanks
-00+30
16 35 (VG-HODY) (AVE G ON)
thc-armed
RHC-ARMED
F 16 85 (VG-PORY)
MONITOR LM IGNITION
( 126 + 19 + 40)
4 •»«»*«««* ft
LM COH BURN
(-l*9+0»4« 1)
««SETUP pcs CJDH 8aCKUP«4
BMAG mode ( 3 ) -ATT 1/RATE2
AUTO.RCS SEL A/c R0LL(4 )-MNA
<»«AUIGN GDC TO IMu «4
KEY V16N20E
“16 20 (R,PyY)
ATT SET thumbwheels TO N?o
FDAI SELECT-1
null ATT ERROR NEEDLES
4 «■
# IF lm Cannot perform the burn *
4 «4444«4«44444«»««4«t4«44«tt**«4 4
4 csM Backup Cnn burn «
( 2 . 2 , 0 . - 2 . 7 )
(0,239/151,0)
4 #««« 4 -» 4 « 444 * 44444 ««# 44*444444 «
THc-Nui L VGS *
« THC-LOCKED 4
MISSION G detailed PROCEDURES
- 95 -
PRO
F 37 BB «
(CONTINUE DETAIIEO PROCEDURES^*
BUT delete P76) *
confirm LM burn complete
pRo(To 'B ypass csm-cdh burn)
F 37 BB
RHC-LOCKEO
AUTO RCS SEL A/C ROLL (A) -OFF
BMaG mode (3) -rate 2
P76 key 76E
F 06 84 (OVtS OF LM CDH BURN)
load (- 1 . 9 / 0 , 4.1)'
PRO
F 06 33 (GeTI of COM 0URN)
load LM CUH GETI
(126+19+40)
PRO
F 37 HB
MISSION G detailed PROCEOURES
-96-
* PftCCEOURES FOR
♦ CDH Thru tfi ^
###«♦« tt «*«* <MH»* «•»♦»* •»<»# HHHt <•■«■»<»*<»■» ft «*««■« ->H» * +M»‘ # «
♦23 (126*23)
ftftTARGET CSM TPI BACKUPft*
P20 KEY ZOe '
F 50 iB (COrtMANDEU R,P,Y) +36
PRO
06 18 (COMMANOeO RtP^Y)
mov£ to leb during
AUTO maneuver
F 50 16 (COMMANDEO R*P,Y)
(0,232/133,0)
KEY ENTER
(126+2A)
KEY V57E •
F 51 88 (PuEASE VAHK)
key V87E (VHF RANGING)
2ERO OPTlCS-OFF
OPTICS mode-man
ohc-cfnter lm in SXT
- make a marks in next
3 minutes (IMCORPoRATF. 3)
OPTICS MOUe-CMC
♦29 (126*27)
KEY V53E(REIMTIALIZE W MAT)
*32 (126*30)
■ PRO/PROCESS LAST MARK
P34 key V37E34E
F 06 37 (GETI-TPI)
load tpi tig
<126*56*27>
♦ 39
*47
MISSION G detailed PROCEOURES
pRO
F 06 55 {*00000, ELANG»CENTAN6)
LOAD R2 - *208,30(DEG)
load R3 s ♦130.00 (OEG)
PRO
F 16 45 (MKSfTFIf-OOOOl)
PRO
F 06 37 (GeTI-TPI)
COPY OftTA ON CHECKLIST
(126+34)
SUNDOWN
P20 KEYV37r20E
key V 57 E^
F 51 bb (Please mark) - ■ ■ '
KEY U87E
OPTICS mode-manual
OHc-CENTER lm in SXT
take -U marks in '.next
11 minutes ‘
(126+37)
COPY lm tpi TlON ON CHECKLIST
(126+45)
PHO/PROCESS LAST MARK
zero optics-zEro
OPTICS MODE CMC
MOVE TO CMD SEAT
«*VERIFY 0RDEAL<»«
kEy V83E
F 16 54 (RfRDOT, THETA)
ADJUST FDAI 70 THETA
pRo
F 16 45 (MKS,TFI ,-OOOGl )
-97-
4>46
(126+46)
P34
F 06
F 06
F 16
F 06
F 06
F 06
F 06
F 16
F 37
KEY V37E34E
37 (TPI TIGK)
load LM TPI TIfsN
Il26+5e*27)
PRO
55 (♦oOOOOtELAN6tCEKTANG)
load r2 s +000.00
PRO
45 (MKS,TFlf-OOOOl>
pro/fake final pass
55 (+00000* ELANG, CEnTANG)
COPY DATA ON CHECKLIST
PRO
5B (HP*DVTPI*DVTPF)
COPY DATA ON CHECKLIST
PRO
81 (VG-LV)
COPY data on Checklist
PRO
59 (VG-LOS)
COPY DATA ON CHECKLIST
PRO
45 (MKSiTFI*MGA)
RESET MDC ET WITH TFl
counting up
PRO
+ SS
♦53 (126+51)
*+MANEUVER to TPI bACKUP ATTlTUDE^^
P40 KEY 4f)E
F 50 l8 (COMMANDEO R,P,y)
KEY V56E
PRO
06 18 (Companded r»p*y>
MONITOR maneuver
F 50 10 (Commanded r*p»y)
<0*191/5*0)
copy LM TPI PA0(P76)
(126+53)
ooSeTuP SPS TPI BACKUPOO
ems MODE-STBY
EMS FUNCTION-DV SET
LOAD TPI BURN VC
' EMS FUnCTION-»Dv
FOAI S^ALE-5/5
rate-high
RMC PWp DIRECT (BOTH) -MNA/MNb
8 WaG mode (3)-ATT1/rAtE2
TVC GmBU DRIVE(B0TH)-AUT0
AUTO Res SEL A/C ROLL (4)-MNA
RHC-^armED
align ii/C TO ZERO ROLL
PRO
06 18 (Commanded R*PtY)
MONITOR ATT TRjM
F .50 18 (Commanded r*p*y)
««gdc align<h»
ATT SET thumbwheels TO N18
FOAI SpLECT-l
null ATT ERROR NEEDLES
ON FDAI 1 with ATT
SET THUMBWHEELS
FOAl SELECT-1/2
ATT SET-GDC
MISSION G detailed PROCEDURES
-98r
gdc align pb-push
ATT SFT-IMU
KEY ENTER"
F 50 25 (002049 6KBL DRIVE TEST)
key ENTER
06 40 (TFitVGfDV)
ov Thrust a-normal
thc-armed
+59+25
dsky blanks
+59*30
06 40 (TFl»VG*DV) (AVE G ON)
EMS mode-normal
♦59+55
F 99 40 (TFitVQtDV)
0 ( 126 + 58 * 27 )
monitor LI^ engine ieNITl(}N
lm tpi BuHn
(21«8*"0tl»«I 1«0)
4H* «««<»* tttt* <HHt « wo *■»»*■»# «
« IF LM Cannot perf()rm 'the burn «
* MN bus tie (2). on (UP) «
'tt NOnESS 'BUS-MnA ' ■»
» SPS HE VlV (aOTM)-AUTO
o SPS HE VLV T8‘ (pOTH)-PP *
« VERIFY SpS Th (iTrOpF »
«« 00*15 ' , ■ ^
THC-APPLY ULLAGE
■tt GMRL MTRS(4)-0N (SEQUENTIALLY)^
« TVc SERVO PWR 1 -ACI/MnA »
« TVC SEoVO PWR 2-AC2/MNE
# PRO «
« 0*00 *
<t csm tpi backup burn •
(-22. 3,0.1 ,10.9)
(0»208/5VOT - *
•ft *
« *
«+oo+ot *
06 40 (TFC*VG90V) *
* THC-TERMINATE iULLAGE «
* MONITOR SPS BURN <»
« F 16 40 (TFCtVG»DV) ^
« Dv thrust A-OFF *
GMBL M^RS( 4 )- 0 fF/SEQUBNT 1 ALLY<»
-» PRO *
F 16 85 (VG-RODY) «
« THC-NULL VGS <»
•» THC-LOCKED *
« EMS MOnE-STBY «
« tvc Servo pwr<boTH)-off «
« MN BUS TIE (BOTHI-^OFF ®
^ SPS HE VLV (BOTH) -OFF ^
« noness bus-off *
PRO
F 37 Bb «
(Continue detailed procedures*
* BUT DELETE P76) »
CONFIRM LM BURN COMPLETE
MISSION G OETAILEO EROCEnURES
-99-
P76
key V37E76E
F 06 04 (DV*S OF LM TPT 0URN)
RHC-LOCKEO ,
THC locked
FOaI SCALE-5/1
RATE-LOW
ROT COM PwR DIRECT (ROTH)-OFF
BMaG mode (3) -rate 2
TVC GImBAL DRIvE(B0TH)-OFF
EMS FUNCTION-VHF RN6
EMS MODE-VhF R^(5
VHF RNG-RESET
LOAD
PRO
F 06 33 <6ETI OF TPI 8lJR^)
load LM GET-TPI
♦12 SECS
(126+58+J9)
PRO
F 37 RB
MISSION & detailed proceolres
« *
- 100 -
PROCEDURES For « +1^ (127+10)
TPI THRU TPF
'♦2
»«maneuver to SXT TraCK«<^
% ' *
P20 key 20E '
F 50 IB- (COMMANDED H»P,Y)
PRO
06 18 (COMMANDED R,P,Y)
move to leb during auto
Maneuver
F 50 18 (COMMANDEU R»P*Y)
(0,246/39,0)
KEY enter
+12+00 (TIGN-3.0
F 06
F 06
F 16
4«target csm mCci' Backup**
F 37
LOSS OF SIGNAL
PRO/PROCESS LAST MARK
45 (MKS,TFt+-0O00l)
zero OPTICS-ZE'RO
' OPTICS mode-cmc
MOVE TO COMMAND" SEAT
MIN)
PRO/MAKE final pass
01 (VG-LV)
COPY DATA ON CHECKLIST
PRO
59 (VG-LOS)
COPY D7TA ON Checklist
pRo
45 '(MKS»TFI »MGA)
PRO '
P35
KEY V37E3SE
COPY LM MCCl PAD <P7'6)
F 16
45
(MkS,TFI,-00001 )
(time from tpI)
(127+11)
SET- LEB ET TO TFl,
OAl
key 41E
COUNTING UP
F 50
18 (COMMANDED R,P,Y>
ZERO OPTICS-OFF
KEY ENTER (BYPASS MNVR)
♦ 4
(127 + 02.)
06
05 (^G-eOnY)
KEY -V93E (REINITIALIZE W MAT)
* ^ '
KEY V57E
«<»SET up.' MCC l' BACKUP**
F 51
Bti
(PLEASE MARK)
key V87E (VMF RANGING)
♦14+25
*
OPTICS mcoe-man - -
‘OSKY BLANKS
OHC-CENTER LM IN SXT
+14+30
'
make 8 MARKS ly next
16
85 (VG^BODY) (AVE <G ON)
b MINUI'ES
THC-ARMED
(127+06)
RMC-'ARMEO '
MISSION G detailed PROCEDURES
- 101 -
♦IS (127+13+27)
F 16 85 (VG-fiODY)
4 4} '4 4 « '<(’ 'll -<V ft M 'H' « ^ ^ ^ ^ ^ «
LM PERFORMS MCC] BU«N
4 4 4 4t « 4> 4^ 4^ 4 # 4 <H> 4t 4^ tf 4 4 4^ 4 4^ 4^ 4} ^ ^ 4^ ^ ^ ^ 4^
4> 44 4 « * 4 4» 4» <H» 4» 4» 4 4» 4t 4 4» 4 4 4 4» 4 4 -4 4» 4» 4f 4 4 4Ht 4» 4 4t tt
CSM MCCl BACKUP BURN
(0f266/l8,0)
44444444444 * 44*444444444444444444444
+ 27
confirm lm burn complete
PRO (TO BYPASS CSM-MCCl BURN)
F 37 B0
thc-lockeo
RHC-LOCKED
Pt6 key 76E +27
F 06 84 (DV + S OF LM MCn BURN)
LOAP I.M MCCl D\/,S
PRO
F 06 33 (GeTI oF MCCl Rt)PM)
load lM GET-MCCl
(127+13+27)
PRO
F 37 RB
MOVE TO L£H
««TARGET CSM MCC2 8acKUP44
P35 key 35E
F 16 45 (MKS,TFI, -00001)
ZERO OPTICS-OFF
OPTICS MCDE-CMC
+ 28
+ 28-
♦18 (127*16)
' MISSION G detailed procedures
key V93E (REINITIALIZE W MAT)
key V57E
F '51 BB (PLEASE MARK)
KEY V87E(VHF RANGING)
omc-center LM IN sxr
OPTICS MOOE-MAN
make 9 MARKS I'N -NEXT
(127*21)
9 MINUTES
SUNUP
(127+25)
F 16 45
pRo/process last mark
(MARKStTFI*-0000l)
zero (7PTICS-ZERO
MOVE TO COMMAND SEAT
(TIGN-3,0 MIN)
pro/make final pass
F 06 81 (VG-LV)
COPY D“TA ON checklist
PRO
F 06 5g (VG-L0S>
COPY DATA ON CHECKLIST
PRO
F 16 45 (MARKS+TFI+MGA)
PRO
F 37 Bb
(l27+27)
COPY LM MCC2 PAD
30
P41' key 41E
F 50 i8 (Commanded R.pj'v)
key V56E
- 102 -
♦ 29^25
*30
KEY ENTER<0YPASS MNVR)
06 85 (VG-BODY)
♦ 32
•imvMANEUVER to COAS track ATTITUrjE««
"♦set up mcC2 Burn*"
dsky blanks
16 b5 (VG-BOOY) (AVE G ON)
THC-APNED
rhc-armEo
U27+29 + 27)
F 16 85 (VG-BODY)
LM performs MCC2 SuRN
■»♦«*•»*♦♦♦♦♦♦♦♦♦♦♦♦«♦♦♦♦♦♦♦""
csM MCC2 Backup burn
(0*300/7»0)
«■»«•»##<»«♦«««♦■»♦♦♦♦♦*■«■♦♦«♦«■»■♦♦♦♦♦*♦* +34
POO
key ooe
kEy V89E
F 04 06 {U0003»00001»BLNK)
LOAD R2 = 00002
PRO
F 06 18 (Commanded R»p»y)
PRO
F 50 le (Commanded r»p»y)
PRO
06 18 (COMMANDED R*P,Y)
move to cmd seat
DURING AUtO MANUVER
F 50 18 (Commanded riPiY)
(0,275/330*0)
key enter
confirm lm BUHk complete
PRO (TO .BYPASS CSM-MCC? BURN)
TMC-LOCKEU
RHC-LOCKEU
F 37 BB •
P76 KEY 76E
F 06 04 (OV*S OF LM MCC? BURN)
LOAD LM MCC? OV,S
PRO
F- 06 33 (GETI OF MCC2 HliRN)
load lm GET-MCC?
^ (127+28+27)
PRO
F 37 B6 ^
MISSION G detailed PHOCEDUPES
-1Q3-
« PROCEDURES FCR SRAKiNG »
<} •» 4 # 'tt 'tt 'ft ^ ^ 'ff ^ It O' -tt 'tt' -tt '<>’ 4 ‘A St 4 -it 'tt it it ‘It 'A 'tt « 'tt 'tt 'ft « ^ 4|i « ^
RHC-ARMEO
CENTER LN IN RETICLE
BMaG mode (3)-ATTI/RATE 2
MONITOR EMS FOR RANGE
♦38 (127*36)
P47 key V37E47E
F 16 S3 (0V-80DY)
KEY VB3E
F 16 54 (R,RDOT»THETA>
THC-ARMEC
monitor lOs control
monitor r and r dot
ft ft ft ft ft ft ft ft ft ft ftiHHt ft ft ft ft ft ft ft <t ft ft ft ft O- ft
4 ft
« BRAKING GATES AND RET ANGtS «
ft ft
ft 30FPS,-AT ftOOOFT. (1,00NM>-.13 dEg »
ft EOFP'S AT 3000FTi( ,50NM>-.26 DEG »
ft' lOFPS AT l500FT.-( .2 SNm)-,54 dEG ft
ft 5FPS AT S00FT.< .08NM>-1.6 DEg ft
ft aOOFT^'t ,05NM)-2,7 DEG ft
ft 200FT.( ,03NM)-4,0 OEG *
ft IOOFT. ( ,02NM>*B.5 oEG «
ft ft
ftftftftftftft*«ftftftftftftftftftftft44*tft4ftitiH»*ftiMtft.ftft
USE range on dsky to check ems
range Indicator, use
reticle angle as third
vote;
U27+4O+30)
ft ft 4 ft ft- 4 * 4 ft 4 it 4 ft 4 ft 4 ft ft ft 44 ft ft ft ft o 4 44 tt 44 ftft ft
TPF
4 ft ft ft «■ ft ft ft ft ft ft ft 4 ft ft 4 4 ft ft it it 4 ft ft ft ft ft ft ftft ft ft ft ft ft
MISSION G detailed PROCEDURES
-105-
5^reced!ng page blank not filmed
6.3 P20 NAVIGATION SUMMARY WITH SUN ANGLES
IT - INITIATE TRACK
CT - CEASE TRACK
X/Y; X = NUMBER OF MARKS
Y = MINUTES IN MARKING PERIOD
SUN ANGLE
{LOS TO SUN)
GET
EVENT
DEGREES
124:30:39
LM INSERTION
124:36
SUNSET
124:49
IT (SXT/VHF) (V93,5/5,V93, 15 VHF/15)
124:54
CT (SXT)
125:09
CT (VHF)
125:21:20
LM CSI
125:22
SUNRISE
125:29
IT (SXT/VHF) (3/3;V67, 02000, 00020
00001 ;18/18)
173
125:34
172
125:39
158
125:45
141
125:50
CT
126
125:50:40
LM PLANE CHANGE
125:53
IT (SXT/VHF) (3/3,V93,9/9)
117
125:59
99
126:05
CT (SXT/VHF)
81
126:19:40
LM CDH
126:24
IT (SXT/VHF) (3/3,V93,2/2)
26
126:30
CT (SXT/VHF)
9
126:34
SUNSET
126:34
IT (SXT/VHF) (11/11)
126:45
CT (SXT/VHF)
126:58:27
LM TPI
127:02
IT (SXT/VHF) (V93,8/8)
127:10
CT (SXT/VHF)
127:13:27
LM MCCl
127:16
IT (SXT/VHF) (V93,9/9)
127:21
SUNRISE
97
127:25
CT (SXT/VHF)
97
127:28:27
MCC2
127:40:38
TPF
ORDEAL AND INERTIAL GIMBAL ANGLES (DEG)
ORDEAL AND INERTIAL GIHBAL ANGLES (DEG)
.1Q8-
7.0 LM RES-CUE CASES
Numerous rescue cases occur for Mission G caused by a deci-
sion to abort the mission. These cases are either CSM passive
where it is only necessary to monitor and back-up the
LM activity or CSM active where it is necessary to rescue
the LM. Investigation of the possible situations which
might occur and the need for procedural support of these
cases has led to the need for defining fifteen possible
rescue cases. These cases are discussed in the following
sections.
It should be noted that the particular rescue cases
discussed in the following sections were based on the
operational trajectory presented in Reference 8,2. The
times have been adjusted to reflect the new operational
trajectory given in Reference 8.18; however, the burns
were assumed to be unchanged.
-109-
7.1 Partial DPI (<25 FPS) (CSM Active)
7.1.1 Summary
This rescue case provides for the situation where the LM
app,lies less than 25 feet per second of the DOI burn and
cannot perform a direct return. The CSM performs a
height maneuver one rev after DOI, This height maneuver
is a Rescue II burn and is targeted for a delta height
of 10 nautical, miles one half rev later. . CSI.| occurs one
half rev after the height maneuver and is a retrograde
burn. The CSI burn lowers the CSM apogee allowing the
CSM to catch up to the LM. A CSI 2 burn (nominally zero)
is scheduled halfway between CSI.j and CDH. CDH occurs
one rev after CSI.| and results i,n a delta height of 10
nautical miles. TPI occurs on a CSM elevation angle of
208.3 degrees
The relative profile and the burns shown in the following
pages represent the particular situation where the LM
applies 20 feet per second of the DOI burn. This data
for other partial DOI burns will vary although'
the same basic checklist may be followed.
7 I 3 fARTIAL 001 (
IH WATMA MJflO
VHf
ONLY
V93,
(34) (OPTIONAL)
COPY
1 Y93>^
- . RESCUE TVO
V93,V87.(VHF 0KL7)
0 Ihokortzoxau
^0 10 2
2 iV APPLIED AT DOI
P41 (trPASS HHVR}.RCS setup, EDC ALI6N
s mi anyT iin tTiti
■ IF VHF,V93, VHf ONLY ;
5H.?l9-Yy£i,^§§i§5!-2!!tL'
P32 FIHAL COMP T*"
P40 (150*)C180,164/101.0)» V56. SPS SETUP | COHSiLrably^ I
CSH CSI 0NE(104 37 05j(“55 6>P>0)(180, TBO/101.0)
ROLL 160* TO ( 0 , 192 n 01 » 0 )
PS2 {OPTION 3)
P20 (lS5*)(U.AS/25fi,0)
P32. CdHPlTTE CSI TWO TIGM, H»1
[5j ^
— V» <CSI1)
V93,V57,VB7,SXT/VHF(5)
-TERMIKATE SXT»V93,VHF[S),
ir90<HARK TO CSI TWO -9)
fiF’*v hfV V 93T vTif ■’ohlV" " ’
.IF NO VHF» V8a» 5XT ONLY
ItTiTfWiP JiT/irtilWE W-fFTOI
til*)
Lp32 f COUP
P41 , V56. RCS SETUP, EOC ALIGN
— ICSN CSI TMO(105 34:261(0.95/197,0)1 , P76
■ — P2Q {0,116/207,0) V57, V87, 3 NARKS. V67 (♦OZOOO.+OOOZO. + OOOOI )
^ (13)
VHF
Lv90 (CSN)
P30
P41. V56. RCS SETUP. 60C ALIGN
CSh PLANE CHANGE
■ L^ PZO (13«)(Q.20B/E09.0f. P33 ,
^ (Sp *57. *®7. 3HARKS,_V93
P33 final CCNP, V90 (CSH) ------------
I NOTE CDH A* VARIES I
P40 (117*)(0, 350/287,0), V5G, SPS SETUP j CONSIDERABLY J
ICSH CDH(106-^I ■W(6M.0.-4 3)(D.4/287.0)| , P76
PZO O43’)(0, 240/144,0)
P34 {ELEVATION OPTION)
■V57, VS7, AFTER 3 HARKS. V93 . V32
S*7
VHF (19)
L.pj4 fihaL conp lh tpi tisk
P40 (S3”) (0,189/18,0)
HC5H TP1(107:06 layriA S.0,7 5){0, 207/16,0 ) I . P76
720 (29»)(0.250/47.0) .... . „ „„
VKMiMj-P3S FINAL CCtf
-VM, V57. V87
H0,2«5/29.0i], PT6
SAT {ij *57, V87
VHF r-i-P35 FINAL COHP. P41 BYPASS HNVR
:nnjTOairi>iHJKi3;i
P35 (P20)
POO, V89 (37*) (0,278/343 ,Q)(0, 300/20,0)
P47, V83
- 112 -
7.2 Partial DPI (>25 FPS) (C5M Active)
7.2.1 Summary
This rescue case provides for the situation where the
LM applies more than 25 feet per second of the DOI burn
and cannot perform a direct return. This case is
identical to the Partial DOI <25 Rescue except that
there is one more rev between CSI-j and CDH and conse-
quently an additional CSI burn. CSI 2 (nominally zero)
occursi one rev after CSI-j and CSI^ (nominally zero)
is scheduled halfway between CSI 2 and CDH.
The relative profile and the burns shown in the following
pages represent the particular situation where the LM
applies 60 feet per second of the DOI burn. This data
for other pa'rtial DOI burns greater than 25 feet per
second will vary although the same basic check-
list may be followed.
- 113 -
7.2.2PARTIAL DOI (i25 FPS) (CSM ACTIVE)
CSH
ABOVE
723 PARTIAL BOI (225FPS) (CSN ACTIVE)
-1U-
— Ilm PARTIAL DPI (101 • 38 -A 9 )| .P 76
!ZLJ!£L.P20 {TttlN)(0.234/314,0)
'V93. V87 fVHF ONLTHHARK TO DOI +43)
VHP
ONLY J34) OPTIONAL
ROLL IM" ANO PITCH UP 114° (100. 274/213,0), V64, ACQ R5FN
■HCC-H UPLINK (LH VECTOR) P20 (TRIHH180, 303/213,0)
3-V93, ¥87 (VHF ONIYXHARK TO RESCUE -16) £
XcOPY RESCUE TWO PAD ‘
=■-40
<3
(37) OPTIONAL w
2 AY APPLIED AT DOI - FPS
P40 (167°)080.I54/282,0), SPS SET-UP. GDC ALIEN
I CSM RESCUE (103 37 - 5 <t )(-45 8 ,ci]o)(iao.iao/ 2 a 2 ,o) I
P20 (128P) (180,331/50,0)
P 32 , H -4
l*V93.V57,V87,SXT/VHF(5), TERMINATE SXT,V93 ,VHF ( 5 ) ,V 90
.(MARK TO CSI OHE-16)
_„an ^IF VHP, ¥93. VHF ONLY ’
IF NO VHF. VSa.SXT ONLY
(31) !• - -' -i
I NOTE CSI AV VARIES I
1-P32 final COMPiACQMSFN I CONSIDERABLY ]
P40 (178")(18'‘ .162/101,0), V56, SPS SET-UP, 5DC ALIGN
- 4CSW CSI ONE (ld>l-35 49)(-5S 4.0.0)(ia0.1BO/101,0)t .P76
-P52 (OPTION 3), GDC ALIGN, VERIFY ORDEAL (V83)
-HCC-H UPLINK (LH VECTOR)(IF LH ACTIVE)
-P20 (83»)(I80, 328/184,0)
■TT— V87 (VHF ONLY) , 3 HARKS, V93 (HARK TO CSI ONE +38)
(15) OPTIONAL
V93, V57, V87.SXT/¥HF(5). TERMINATE SXT.Y93, VHF(5), Y90
(mark to CSI TWO - 9 ) .
V^O JF VHF, V93, VHF ONLY
;5) fF HO VHF. V88.SXT ONLY))
P32 FINAL COHP, ACQ HSFN
P41, V56, RCS SCT-UP, GDC ALIGN
CSM CSI TWO (106 27-5B)(180, 339/261,0)
P20 (3rX)80,320/Z30,0)
:P32, COMPUTE CSI THR£ET1GN,N-1 , ,
I — V93. V57.V87.SXT/VHF (5), TERMINATE SXT. V93, VHF (5), V90
D 1 (HARK TO CSI THREE -9 )
— V90 (csH I — — r — — "i
IF VHF,V93,VHF ONLY 1
■IF NO VHF. V 88 .SXT ONLY •
41) '- -
— P32 FINAL COHP
-P41, V66, RCS SET-UP, GDC ALIGN
CSH CSI THREE
Mr-vM-wMa
P 41 , SETUP, GDC ALIGH
68 B,0.-S.4)(0,5/287,0
'P34 (lEoym-Ko.eAs/Hi.o), (aEV option)
-V57,V87, 3 HARKS. V93, V32,(MARK TO TPI-13)
_RECALL P34 KITH LH TPI TISH, FINAL COHP
P40 (61°)(0.182/11,0). VSG, SPS SET-UP, GDC ALGIN
0,250/49/0), P35
V93, V87, V57 (HARK TO TPI +12)
P35 FINAL COHP
P41 BYPASS mVR
III'! I— II I ■! irf« 0 ^ 3 !ga!Dl 1
(1Q«
V89 TO COAS TRACK (38 ) (0,283/341,0)
P35 FINAL
•25_Ayio:
P32, COMPUTE CSI TWO TIGH. N«2
-115-
No PDI^ + 12 {LM Active)
7.3.1 Sutirniary
This situation arises when a failure prevents continuation
of the planned mission after DO I and the LM initiates
rendezvous with the CSM. The LM phasing burn is applied
12 minutes after nominal PDI^time and is targeted by the
ground or obtained from onboard charts. The CSI maffeuver
is applied one-half revolution (LM) af.ter phasing and the
CDH maneuver is one-half rev later. TPI occurs approximately
40 minutes after CDH at a delta altitude of approximately
15 nautical miles and is targeted for a LM elevation angle
of 26.6 degrees. The LM CSI burn is nominally zero; however,
if it is necessary for the CSM to apply this burn, it is
not nominally zero even though it is targeted for the LM
CSI time.
103 00-
104 OO
P20 (2M{0»249/330.01
r<0*G0 LH PD]
UDl) 41ZAKIRT(102 47 14)(I1& CSH (0.]S/Z71,0)|,P76
P00» PITCH VP 90* (0»n4/’l .0], V64 ACQ K6A
PS2 ]0pt1on 3)
^HCCwH UPLINK (LH VECTOR)
“P20 (12ftM*0. 19/233,0)
04TAIX CSI AND T^r TICKS
V93.V57, VB?
SXJ/vmt* TEWIKATE SXT, V93,
VHF(5). MO, VHF(9) -
WaKTOCSI-9 ' IF VHF V93, VMFONtY 1
* IF KO VHP, VSfi, SXT ONLY '
V90 (CSH AXD IK)
P32 FINAL COMP
COPY LN CSI PAD
P41 BYPASS, V56, ftCS CHECKLIST
IH CSI O03J33 00)(o 1,0. o> I'’’'®
CSM CSI »S_6.0.0)(0 42/<59,Q)
-P20 (TR1}1M0,45/1SS,0)
— -V57, va?,
3 SX7 HARKS, V67 (402000,^00020,^00001)
(HARK TO PLAHC CHANGE -1 >
-V90 VOICE U YOCT TO LN. COPY LH PC PAD
IlN plane CHANCE <104 04*2571 . P76
P33 (P2OHO.128/M5,0)
^118-
7.4 No PDIg + 12 (LM Active)
-7.4.1 Summary
This condition arises when the first PDI opportunity i.s
passed due to some difficulty, but the difficulty is of
such 'a nature that it is desired to try to initiate PDI
at the second opportunity. If.it is obvious at this
time that the problem still exists, the ,LM initiates an
abort. At 12 minutes after PDI 2 time, 'the phasing burn
is applied. This burn is ground targeted or based on
onboard charts. The CSI maneuver is applied one-half rev
(LM) after phasing and the CDH maneuver- is one-half rev
later. TPI occurs at a delta altitude o'f 15 nautical miles
and is targeted with a LM elevation angle of 26.6 degrees.
The LM CSI burn is nominally zero; however, if it is
necessary for the CSM to apply this burn', it is not
nominally zero even though it is targeted for the LM CSI
time.
1 .k.l.
33
8l
33
13
75
81
NO PDI 2 + 12 (LK ACTIVE)
-120-
sxr
WF <23)
- ll-M PDl AB0RT(10<I 6.0.112 Qlb 76
-BOLL (180*)(I80. 21/268,0)
fS2 (OPTION 3), SDC ALIGN
-MCC-H UPLIXKiLH VECTOR AND CSH VEC
RECEIVE C5I And TPI ticns fron lh
-COPY IN CSI PAD
-P4I (24“) (180,163/292,0) V56, RCS SETUP,
GDC ALIGN
, LN CSK105 29-23) 0,0,0) [• F76
CSH esi (103 33 06)(-6 a.D.01(180.180/292. 0l
P20 (14V) (140,350/73 ,0)
-V93,V57,V87
(MARK TO PLANE CHAHGE-1)
V90, VOICE LH YDOT TO L«,
COPY LH PC PAD
' LN PLANE CHANGE (106-02 5511 ■ P76
y57,V87, 3 SXT HARKS, V67
(tOZOOO, '''00020,400001)
(RANK TO COH-15)
+47.
107 0(1
sn
ynr (s)
-V90 (CSH AND LK)
-P33 FINAL COM>
-MU 180* (0,119/78.0)
-P40 (152*)(0, 278/230,0), V56j SPS SETUP, GDC AUG*
LN CDM( 106:31 :55){-139 4,0,-362 2)|*
CSH (144 0,0,342 8){0, 293/230,0)
-P20 (92*)(0, 238/138,0)
-P34 (ELEVATION OPTION)
-V67, V87, 3 HARKS. V93, V32
-COPY LH TPI TICK
-P34 KITH LH TPI TIGM. FINAL COM
-P40 (4«‘)(0. 186/15,0). V56
COPY IM TPI PAD, SPS SETUP. GDC ALIGN
LH TPI(107:12-17X22 2.0. -II 2) !•
CSH TPI (-22 0,0,9 3)(0,203/15,0)
P20 (26*)(0, 247/41 ,0), P35
V93, V57, V87 (HARK TO TPI 4 12)
P35 FINAL COP, COPY LH MCC1 PAD
F41 BYPASS
LH HCC1 (107 27:17) 1, •’76. •’3S
CSH HCC1 (0,264/20,0)
■' ■ 'in, V57, V87. (MARK TO TPI + 27)
P35 FINAL COHP, COPY LH HCC2 PAD
P4I BYPASS
. LF7iccr7To7T2T7ri • ’’’*•
CSH NCC2 (0,300/13.0)
V09 TO COAS TRACK O4'>H0.3»l/359,0)
V47. V83
- 121 -
7.5 < 60 No PDI^ + 12 (CSM Active)
7.5,1 Summary '
I '
This situation occurs when the LM is completely inactive
following the DOI burn or applies less than 60 feet per
second of the phasing burn, i.e., the LM cannot apply
the PDI burn' nor can it complete the rendezvous. Under
this condition, the CSM may accomplish the entire
rendezvous. The first of the series of rescue burns
is either ground targeted or taken from an onboard chart.
This burn occurs at one rev after the DOI maneuver. A
CSI^ burn is applied one-half rev later and is targeted
with -a CDH to occur two revs later. A CSI^ burn
(nominally zero) is scheduled half way between CSI^ and
CDH. A third CSI (CSI^) again nominally zero is scheduled
half way between CSI 2 and CDH. The CDH burn ss targeted
for a differential height of 10 nautical miles and the TP I
burn is cued on a CSM elevation angle of 208.3 degrees,.
The relative profile arid the burns shown in the following
pages represent the particular situation where the LM was
not able to apply any of the phasing burn. This data for
all cases where a partial burn less than '60 feet perj
second is lapplied will vary although the same basic
checklist may be followed.
- 122 -
M CSi TWO
06 : 26 : 28 )
, 0 , 0 )
.35/319,0)
LM PHASING.
(102: if6:39)
2 0 0
CSM CSl ONE
( 10 ^: 35 : 22 )
(-61.4,0,0)
( 180 , 180 / 102 , 0 )
_
CSM RESCUE
(103:37: 49)
(- 57 . 0 , 0 , 0 )
( 180 , 180 / 289 , 0 )
13
75
61
CSM COM COPY
84
33
LM. CDH . P ? 6
CSM TP1 COPY
84
33
12 ltS« ACTIVE)
- 123 -
J P32 FINAL CONP
P41. V56, BYPASS KHVR. PCS SETUP. GDC ALIGN
iftu f ;;} TU011D6 26:281(0.35/319.0)1 , P76
P20 (!6”HO,27/303,O)
P32 COMPUTE CSI THREE TIGM, N-l
VJ3, V57. V87
-V90 (CSN)
"SXT/VHF (5). TERMINATE SKT. V93, V» (S).
VM. YHF (31). (MARK TO CSI THREE - 9)
, IF VKF. V93, VKF ONLY ,
I IF NO VHP. V88, SXT ONLt[
■ PJ2 FIKAl. COHP
— ^^P41. BYPASS WVR. RCS SETUP. fiPC ALIM
» |csi CSI THREEno7.2Z.On{0.93/19S:QT] . P76
' P20 (TRIK)
V57.VS7. 3 SXT HARKS. Y67 (V0z000.-K)0020,'r00001 )
(HARK TO PLANE CHANGE -9)
(10)
V90 (CSH)
P30
PAl. BYPASS mat. V56, RCS SETUP, GDC ALIGN
CSM PLANE CHAHGEn07*I|B;W(0.'208/21a.'ol . P76
^=T"P20 (TSIH) (0.205/212,0), pm
1 V57.V87, 3 HANKS, VJ3
nol (HARK TO CDH - 12) ] NOTE. COH iV VARIES
_P33 FINAL COMP, VM (CSM) | CONSIDERABLY \
PAD (176*)(0,3E0/287.0), V56, SPS SETUP. GOC aIiGK' '
ICRII CDH (I0B;I7.1I|)(t 74 9.0.-7 6) (0,5/287.0)1 . P76
-P20 (1A4°)(0,232/1A3,0)((<ANIIAL FItVR 2VSEC TO TRACK
P3A (ELEVATIOH OPTION) ATTITUDE)
' V57. V87, 3 HARKS, V93, Y32
! P3A FINAL COMP, VERIFY ORDEAL (V83)
PAO (60*) (0,164/10.0). V56. SPS SETUP. GM ALIGN
ICSH T PI (IQB S3)(-15 2.0.5 '51(0.200/10.0)1 . P76
P20 (37")i0.2A7/47,0). P35
( yjy yp ypj ^ ,2)
1 — P35 FINAL COW. P4I BYPASS NNVR
^ HCCin09 07 S3)I 0.264/28. oH . P76
V93,V57.V87 (HARK TO TPl ♦ 27)
P35 FINAL COHP, P41 BYPASS HNVR
!Ce2)10q’22 Sl)(0.297/16:^ . P76
P00.V89 COAS TRACK (35*)(0, 267/341 ,0)
P47. V83
rtPF(ios^35 itin
-124-
7.6 > 60 No PDI^ + 12 (CSM Active)
7.6.1 Summary
This rescue case provides for the situation where the LM
applies at least 60 feet per second of the phasing burn
but cannot complete the burn and it is necessary for the
CSM to initiate a rescue. This case is similar to the
previous case except that one less rev is required for
rendezvous since at least a partial phasing burn was
achieved. The initial rescue burn occurs one rev after
DOI and is again ground targeted or taken from- an on-
board chart. The CSI-| burn occurs one-half rev after the
initial rescue burn and is targeted for a CDH one rev
later. A CSI2 burn, nominally zero, is scheduled one-half
way between CSI-j and CDH. The CDH burn results in a dif-
ferential height of approximately 15 nautical miles and
the TPI burn is cued on a CSM elevation angle of 208.3
degrees.
The relative profile and the burns shown in the following
pages represent the particular situation where the LM
applies a partial burn of 60 feet per second. This data
for all cases where a partial burn greater than 60 feet
per second is 'applied will vary although the same
basic checklist may be followed.
-125-
7.6.2. >60 NO PDI.J + 12 (CSM ACTIVE)
HLH PHASING <102-J|6:39)(34 1.0,49 4>|
ROLL 180' TO (180,16/265,0)
P62 (OfTiOH3), SDC ALIGN, VERIFY ORDEAL (V83)
- POO, HCC-H UPLINK (LH VECTOR)
S_20
-COPY RESCUE THO PAD
-P30
100 ZOO
'LM PARTIAL PHASING BURN
PAO, (2A")(iaO,156/23S.O), V56, SPS SETUP. GDC ALIGN
JCSH RESCUE [101 T7-I|9)(-A0 1 ,0.0) CIBD. 180/289,0)1
PRO (n2“)(180,336/61.0)
SXT
VHF
(5)
(5) ^
V
H
F
0
(2S)
N
L
Y
f
■ P3Z (« - Z)
V93,V57,V87.SXT/VHF(5),
TERMINATE SXT,V93 (VHF ) ,
V9Q(HARK TO C51-16)
V90
3F VHF.V93.VHF ONLY I
-PAO (171*)n80. 165/1 01 ,0), V56, SPS SETUP, GDC ALIGN
- ICSH CSl ONE (104!3S-S4)(-70.1 ,0,0)080,180/101 ,0)1 , P76
ROLL IBO' TO (0,189/101,0) f
HOTE
CSI AV VARIES I
J C0NSIDERA8LY I
P52 (OPTION 3), GDC ALIGN, 'VE'RIFY O'RD'EA'L '(VB3‘) ‘
SXT
W
(5)
■PZO (37“)(0,30/64.0)
-P3Z, COMPUTE CSl THO TI6N, N»1
-V93,V57,VB7,SXT/VHF(5),
TERMINATE SXT,V93 (VHP j ,
V90(MARK TO CSI TWO -9)
-V90 (CSM)
■IF VHF,V93,VHF ONLY |
( 18 )
•P32 FINAL COPP
cno>
-127-
7.-7 < 40 No PDI 2 + 12 (CSM Active)
7.7.1 Summary
This situation occurs when the LM is inactive and unable
to apply the PDI 2 maneuver and is’ able to achieve less
than 40 feet per second of the phasing maneuver. Under
these conditions, the CSM initiates a rescue with the
first burn occurring two revs after DOI . CSI-j occurs
180 degrees later with a CSI 2 and CSI^ (both nominally zero
occurring one and two revs later, respectively. CSI^
occurs 180 degrees after CSI^ and CDH occurs three revs
■after CSI.j at a delta altitude of 10 nautical miles. With
this rendezvous situation, rendezvous would be completed
approximately 12 hours after DOI.
The relative profile and the burns shown in the following
pages represent the particular situation where the LM is
■unable ^to apply any of the phasing burn. This data for
all cases where the LM applies a partial burn less than
40 feet per second will vary although the same
basic checklist may be followed.
n (CSK ACTIVE)
• 129 -
-130-
7.8 40-90 No PDI 2 + 12 (CSM Active)
7.8,1 Summar.y
This rescue case provides for the situation where the
LM could not complete the phasing burn after initiating
an abort at BDI 2 . The first rescue burn occurs two
revs after DOI and is followed by CSI^ one-half rev
later. The C$I-| burn is targeted for a CDH to occur
two revs later at a delta altitude of 15 nautical miles
with the CSI 2 burn (nominally zero) scheduled half way
between CSI and CDH. The rendezvous would be com'pleted
approximately 10 hours after DOI. .
The relative profile and the burns shown in the following'
pages represent the particular situation where the LM
applies a partial burn of 65 feet per second. This data
for other dases where a partial burn between 40 add 90
feet per second is applied will vary although the
same basic checklist may be followed.
7.8.2 ^0-90 NO 12 (CSM ACTIVE)
- 131 -
trt O >1 3e*ncJ3C V»0^
783 40-90 NQ PDIj 4 12 (CSM ACTIVE)
HO PDtj 4 12 004) 1)0 4)3)
ROLL 180* (180,21/264,0)
■P52 (OPTION 3)
7--.-JCC-H UPLINK
(L« VECTOR AND CSK VECTOR)
copy RESCUE TWO PAD
50 70 90
LH PARTIAL PHASING BURN
P40 (19°)(ieO, 131/281,0), SPS SETUP, GOC ALIGN
CSH RESCUE(105 36' 2&H -40.3 ,C,0)(180, 180/281 . 0)
I ■ ■ I
I NOTE CSI M VARIES '
1 CONSIDERABLV
P32.N-4 1 CONSIDERAE
U— P40 (179")(180,16]/100,0), SPS SETUP, GOC kiGN
CSH CSI ONE (106-3‘» 34)(-35 4,0,0) (180,180/100,0) ~| > P76
PS2 '(OPTION 3), GOC ALIGN, VERIFV ORDEAL (V83)
P20 (99°)(1S0,32T/199,0)
I ■!. I V57 (SXT ONLY), 3 HARKS, V93
(MARK TO CSI ONE + 45)
'Hp I-V90
-P32, COMPUTE CSI TWO TIGN, K=2
-V93,V57.V87.SXT/VHF{5),
TERMINATE SXT.V93,VKF( 5).
V90(HARK TO CSI THO-9)
(IF VHF,V93,VHF ONLV
-133-
7.9 90 No RDI 2 + (CSM Active)
7.9.1 Summary
This rescue provides for the situation where the LM
completes a partial phasing burn greater than 90 feet
per second. This case is similar to the previous
40-90 No PDl 2 + 12 Rescue except that one less rev is
required between CSI-, and CDH. This rendezvous would
be completed approximately 8 hours after DOI.
The relative profile and the burns shown in the following
pages represent the particular situation where the LM
applies a partial burn of 90 feet per second. This data
for all cases where a partial burn greater than 90 feet
per second is applied will vary although the
same basic checklist may be followed.
7.9.2 >90 NO PDI 2 + '2 (CSM ACTIVE)
-134-
1^20 (21*>(1S0, 358/63,0)
y37.»67,3 XARKS.Ve? <«02000,*000z0 .iOOOOl >
(MRK TO OlAKE CMAHCE * 9)
f41.«SE.IlCS SETUP COC ALIGN
■P20 (S’)(180,!00/108.0)
V57,V87,3 KARKS ¥93
(HARK TO CKO - 15)
P33 FINAL COW, V90 (CSN) j P“FE COH 6V VARIES
ROLL IBO* (0.139/104,0) ACq HGAj_ _ _ ^
PRO (I37*)(q, 293/241.0). V56. SPS SETUP.'gDc'aLIGr''
CSH CDH (t08!Z7 lllHn? T.0. 116.0) Co. 320/2^1 1.0) I , ?%
P20 {96‘)(0. 238/143.0)
P34 (ELEVATION OPTION)
VST, VG7, 3 NANRS. V93
(NAR* TO TPI +47)
P34 FINAL CONP. V83 VERIFY ORDEAL
P40 (7S')(0, 172/3,0), V55, SPS SETUP, HOC ALIGN
TPI (109 0) 33H-2).7.0.5.B)(0.19
P20 (Sr ) (0,243/54,0), P35
-V93, YSr, V87 (NAM TOTPI + Tl)
- P35, FINAL CONP, P41 BYPASS NANEOVER
- ICSH MCCl (log l6-B3)(0.26^/t7TFr
_,P3S
W 3 .VS 7 . V 87 .(NAIK TO TPI + 26 )
P 35 FINAL CONP. P 41 BYPASS HANEUVE R
C 2 ( 10 q ^1 ^^XO. 2 » 1 / 18 . 0 )| . PTE
•pOO, V 89 ( 36 -)( 0 . 255 / 342 . 0 )
-136-
7.10 PDI^ < 10 Variable Insertion {LM Active)
7.10.1 Summary
Th.is rescue results from an abort less than 10 minutes
into the powered descent. Under these conditions, the
LM inserts into a variable insertion orbit. No. rescue
.burn is required for this rendezvous.' The first burn,
CSI is scheduled at 50 minutes after LM insertion with
CDH one-half rev later. ‘
The relative profile and the burns shown in the following
iji •
pages represent the particular situation where the abort
occurs at PDI-| + 10 minutes. This data for. other cases
where the abort is initiated less than 10 jninutes into
t^e descent will vary particularly for the CDH burn.
However, the same basic checklist is applicable'.
7.10.2. PDI, <10 VARIABLE INSERTION (LM ACTIVE)
LM INSERTION
(102:52:20)
LH (103:42: 12)
( 50 . 1 , 0 , 0 )
CSM (-50.9,0,0)
(0, 1 80/268,0) lm plane change
(104:10:53)
LM (105:14:06)
(21 .7, 0,-10. 9)
CSM (-22.0,0,10.3)
( 0 , 205 / 18 , 0 )
7103 POI, <10 VARIABLE INSERTION (LH ACTIVtJ
CHECKLIST CEHERATED FOR ABORT AT PDI| +10
- 138 -
^i3a^
7,11 PDI^ + 12 (10-12.5 Minutes) (CSM Active) '
7.11.1 Summary
This rescue results from an abort during the powered
descent. It is assumed that following the decision to
abort, the UM will be able to insert into a fixed 10 X 30
orbit and that the CSM will then complete the rendezvous.
The initial rescue phasing burn will be performed at a
fixed GET defined as 50 minutes from that insertion cut off
time associated with an abort at PDI^ + 10 minutes. This
rescue phasing burn will be a constant 47.8 feet per second
retrograde burn for cases where an abort is initiated
between PDI-j + 10 and PDI-j + 12.5 minutes. The CSI-j
burn is targeted for the LM CSI time and occurs approxi-
mately one-half rev after .the rescue phasing burn. The
CDH burn is scheduled for 'one rev after CSI-j with a
nominally zero CSI2 burn half way between CSI-j and CDH.
For this rescue situation, rendezvous is completed
approximately six hours after DOI.
The relative profile and burns shown in the following
pages represent the particular situation where the abort
occurs at PDI-j + 12 minutes. This data for other cases-
where the abort is initiated between 10 and 12.5 minutes
.after PDI will vary; however, the same basic checklist
is applicable.
12 (10-12.5 MINUTES) (CSM ACTIVE)
-UO-
CSM
CSI TWO COPY
• •
» *
«
I
•
•
•
«
•
LM
CSI TWO P76
t
«
• *
CSM PC COPY
»
*
♦
t
LM PC P76
1
*
•
«
« *
• •
CSH CDH COPY
7 n 3 PDI, * 12 (10-12 5 KINUTES) (CSH ACTIVE)
P3Z FINAI. COHP
IHSERTIMI (T02 54!32)|
• P52 (OPTICW 3M0. 212/80,0} V48
- nCC-H UPLINK (m VECTOR)
POSSIBLE RESCUE PAD FROH GROUND
— P30
“ F40(171* )(0, 162/269,0). V56 SPS SETUP. GDC ALIGN
CSN RESCUE PHASINS (103 42 17) (-47 8,a.0)(0.16D/269.0)
— P20 (40* )(£>. 150/229.0)
— P32, N-2
-I-V93, V57, VB7, SXT/VHF (5), TERMINATE SXT, V93, VITF (5),V90
llil (5) (KARK TO CS! ONE -12)
“ 7s) riTTHFVVoVrVHV ohlt7'' ”5
V -V90 LIF-KO VHFj V88t. SXT ONLY !
H
F
0 (20)
K
L
Y
-J P32 FINAL COW
— PAD (72*}(0,166/90,0) V56, SPS SET UP, GDC ALIGN,
|C5M CSl OHEdQll 39‘SO)(-3A-a»0.0) (0.180/90,^ , P76
— P52 (OPTION 3)
— P20 (30*) (0,226/60,0)
— P32, COWUTE CSI TW TIGN. N-1
—I V93. VS7, V87, SXT/VHF (5), TERMINATE SXT, V93. VHF (5), V90
^ (S) (PARK TO CSI TWO -9
y Tsi ri?’ VHF,‘V937’VHF'ON'iY'’'''l
H -V90 LIf.NO.
P41, (BYPASS ATT HNVR) V56; RCS SETUP
CSMiCSl Two'll 05: 36-30)(O.O,O) (0,227/316,0)
NOTE IF NO VHF BY CSI TWO -25, V88, CONTINUE SXT)
- P34 FINAL COMP, V83 VERIFY OROEAL
P40 (G1°)(0, 185/346,0), V56) SPS SETUP, GDC ALIGN
CSH TPI (107 12 50)(-23 4. - 3. 10 7) 0,204/346,0)
P20 (37*) (0,248/23.0) . P34
(e) V93, V57 , V87 {HARK TO TPI +12)
P35 FINAL COMP, P41 BYPASS WNR
CSN MCCK107 27 50) (0,263/2,0)
V93. VST, V87 (HARK TO TPI ♦ 27)
P35 FINAL COW. P41 BYPASS HNVR
107-42 50) (0,301/350,0)
POO, V89 ( 35*)<0. 269/315.0)
P47, V83 AT R-1 25 K.M.
TPF (107 53 28
-142-
7.12 PDI-[ + 14:12 (12.5-15 Minutes) (CSM Active)
7.12.1 Summary
This rescue also results from an abort during the
powered descent. This rescue is similar to the PDI-j
+ 12 Rescue except that for those cases from PDI.|
+ 12.5 to PDI^ + 15 minutes, the CSM rescue phasing
burn is a mirror image of the desired LM phasing burn.
Also the CSI-j burn is targeted for a CDH one-half rev
later. However, this CDH burn is not applied but
replaced by a CSI2 which make the two orbits co-ell iptic.
For this rescue situation, rendezvous is completed
approximately six hours after DOI .
The relative profile and the burns shown in the
following pages represent the particular situation
where the abort occurs at PDI^ + 14:12. This data for
other cases where the abort is initiated between
12.5 and 15 minutes after PDI will vary; however, the
same basic checklist is applicable.
LM iNSERTlOH
O02; 56:AA)
7,12.2 PD1^^' Utie
jcs« RESCUE PHASING
(103:A2: 13)
(- 20 . 3 , 0 , 0 )
(0,180/265,0)
LOS
S 0 0
■» 0 0
AESCUE PHASING PAD
LH .CSl ONE P7 6
8A
33
8A
33
.5-15 MINUTES) (CSM ACTIVE)
-143-
CSH CSl TWO
005:36;A5)
(-30.7,0,0)
(0,180/275,0)
AOS
■“-•I..
LOS
CSM CDH
(106:33:25)
(-1 .8. 0,-14. 6)
(0, 97/12 ,0)
50
LOS
3 4a
i 0 9
CSH CSl ONE
(104:38:49)
(- 21 . 2 , 0 , 0 )
(0,180/95 ,0)
CSH PLANE CHANGE
OO6j^05:05)
(0,245/242 ,0)
CSH TP I
(107: 12:38)
(-20.3, 0 ,9.4)
(0, 205/359 t»
CSH CSl TWO COPY
CSM CDH COPY
13
: '
; ;
75
•
;
«
.
J
81
•
.
•
LM CDH P76
•
V
•
84
«
•
LM
CSt TWO P76
33
m •
* »
•
. .CSH TPI COP.Y
— .
1
37
» «
« •
CSM PC COPY
58
•
•
«
•
8!
*
•
•
«
•
59
•
«
»
LH PC P76
LM TPI P76
•
84
*
1 L
•
4 •
33
-IS MINUTES) (CSN ACTIVE)
>13
» -
0
-22
40 .
50 -
-9
106
00 -
0
-23
10
-IS
20 -
0
30 -
+2fi
40 •
50 -
107
+47
00-
0
10-
+4
20 -
+12
+ia
30 -
+27
40 -
♦37
SO •
10 B
00-
■
10 •
-m-
NOTE CSI iV VANieS^
-PS2 FINAL coHP
-P40(70*)(0,l«7/275,0), V56. SPS SETUP, GDC N.IBI
ICSMCSI TWO (IO5-36-T|5)(-30 7,0,0) (0,180.275,0) | ,P76
-P20 (39*) 10.238/3)4,0)
VNF
(13)
"V57. W7, 3 SXT MASKS. V67(*0j000,*00020,+<l0»!)
(MARK TO PLANE CHANGE -9]
Pll.BTPASS MNVR >56, SCS SETUP, 6DC ALIGN
■ ICSM PLANE CHAHeE 110 b ~'05 0 SII 0 . 245 /Z 42 . 11 T 1 .
■P20 05') (0,236/227,0)
-V57, T87, 3
V93
- P33 FINAL CWV. V90 (CSN), ACT) HSFN
-P41 O52°)(0.82/)2.0), V56. SCS SETUP, GDC ALIGN
VHP
ICSM eW(IO&-33 25X-1 8.0.-14.61(0. 97/12,0)1 ,276
P20(125‘’H0. 250/137,0)
P34 (ELEV OPTCON]
VST, *87. 3 MASKS. *93 ,832
(MARK TO TP1-I3)
( 21 )
' P34 FINAL CQNP.LM TPI TIGN, VESIF* OSDEAL (*83)
' P40 (a7')(a,1B7/335,0).V56, SPS SETUP, GDC ALI9(
I CSM TPI(107‘ 12 3^-20 3.0 ,9 *)(0. 205/359. 0)1 . P76
. P20 (32') (0,244/31 ,0). P35
, , , — (*93, V57, *87 (MASK TO TPItI2)
( 8 )
J P3 S FINAL (MWP. P41 BTPASS MAYS
- 4SThcC 1 (107 27-38) to. 284/10,0) I .P76
^ V93. V57, W7 (fMK TO TPl *27)
^ P35 FIHM. coy 4 gtPteSHHVR
jcSHMCC2 (107 42 3^1^ 0.299/358. 0) I .P76, POO
[—*89 C0AS“T11ACK (35*)(0,2J2/323,0)
- P47, *83
(tpf[ 1 07~S3 3gn
-145-
7.13 PDI-| + 21:24 Preferred lift-off (Tg) (CSM Active)
7.13.1 Summary
I *-
This rescue results from an abort 21 minutes and 24
seconds after initiation of the powered descent. This
coincides with the first preferred lift-off time (Tg)
after PDI. The initial rescue phasing burn will be
performed at a fixed GET which is approximately 153
minutes after LM insertion cut off (when the CSM
reaches the longitude where the LM would have done-
phasing). This delay is due to the fact that the CSM
cannot back-up the phasing burn at the LM phasing
time because of the lack of spacecraft communications
at that time. CSI^ occurs one-half rev after the
rescue phasing burn with CSI^ occurring half-way
between CST^ and CDH. For this rescue situation,
rendezvous is completed approximately eight hours
after DOT,
7.13.2.
PDI^ + 21:24 PREFERRED LIFT-OFF (T 2 ) (CSM ACTIVE)
LM INSERTION
(103:03:55)
X
CSM RESCUE PHASING
(105:37:33)
(- 18 . 5 , 0 , 0 )
(0,180/277,0)
1
CSM CSI TWO BURN
(107:34:21 )
(-30.8,0,0)
(0,180/273,0)
CSM CDH
(108:31
(-. 8 , 0 ,
(0,278/
LSI
71]} PDI, + 21 24 PSEFCRRED
-STOP PITCH{0, 20 6/80,0)
- P52 (OPTtON 3)
- kH 1856flTI0H[ )03 03 5S)|
- HCC-H UPLIHIC (IM VtCTOB)
-MCC-H UPLINXtCSH VECTOR)
•COPY RESCUE PHASIHUpAOdP CSM ACTIVE)
■?30
'P40 063') (0,150/277,0), VSE.SPS SOUP, GDC U-IGtl
|CSW RESCUE PHASIHGflOS 37 33)[-lB 5. 0.0) (0,180/277.0)
-147-
V93.V57.V87,S*T/yHF(5)
(S)TERNINATE SXT,y93,VKF(S).
— ■V90(HARX TO CSI TVO -12)
-{so (CSH) SrVHF’vOarVHF OHLv' *1
|F.N0.VHF,V88ji5!(T.aHlVJ
- P32 flKAL COMP
-P40 (87»)(0, 162/273.0) V5E, SPS SETUP, GDC ALIGN
■ ICSH CSI TWO (107-30 2IH-30 B.O.OHO,
-P2Q (24*) (0,210/297,0)
-V87, VST, 3 MARKS. V67 (402000, *00020, *00001 )
itiaQaoai
1-V90 (CSH)
P30
P41, V56, RCS SETUP. GDC ALIGM
FLAKE CHANGE (lOB 02 OB) (0.252/2
tvT l~P2 0 (32*)(0.224/226.0),P33
vS (U)' *{”■ ^ “"'‘S'
‘ " (MARK TO COM - 9)
^V90(CSK)
P33
P4I BYPASS MKVR, V56, RCS SEIUP. GDC ALIGN
ICSH CDH n08*31 08)(- 8.dl'-6.4)j^0.96
' — P20 ( 6B)(Q.222/I19.D)
■ P34 (ELEV OPTIOR)
i V57. V87. 3 WRKS, V93.V32
V*
- P34 FIRAL COMP
-P40 (97*)(0.19«/33G.0). V56, SPS SETUP. GDC ALIGN
1C5H TPI (IDS 06 N6)(-22 2,0,10 TTTO
n P20 (65')(0,247/41,0)
(5) V93, V57; V87
— P35 nUAL COMP, P41 BYPASS MANEUVER
MCC) (iOq 21 1|6)(0.270/26,0) | , P76
VHF (9) ' — V93. VST, V57
1 — P35 FINAL C0MP.P4I BYPASS WIEUVER
1 CSWMCC2 <100 R6-1|6) (0.301/13,0) | . P76
• -POO. V89 <151’)f0.117/164,O)
P47 _V83 ‘
ilTPF (log I|7 44)1
110 00
•>148-
7.14 PDI 2 < 14.5 Variable Insertion (HR Active)
7.14.1 Summary *
This rescue results from an abort during the powered
descent where the descent was initiated at the second
opportunity. It is assumed that following the decision
to abort, the LM will be able to insert into o'rbit and
that the CSM will then complete the rendezvous. This
case is 'similar to the PDI-j case described in Section
7.10. The LM is assumed to achieve a variable insertion
orbit followed by a CSI burn (LM active) 50 minutes
after insertion. The CDH 'burn is scheduled one-half rev
after CSI^ .
The relative profile and the burns shown in the following
pages represent the particular situation where the abort
occurs at PDI 2 + 14:24. This data for other -cases where
the abort is initiated less than 14 1/2 minutes into the
descent will vary parti culaiMy for the CDH burn. However,
the same basic checklist is applicable.
7.14.2. PDl2 <14:30 VARIABLE INSERTION (LM ACTIVE)
- 149 -
CSM
BEHIND
7 U 3 PDIj <14 30 VAftiAOLE INSERTION (LH ACTIVE)
CHECKLIST CEIIERATED FOR AOORT AT PCI, TA
105 00- s
H
STOP PITCH (HAN ATT-RATE CHD AT P-8OHO,212/flO,0)
( 1 . 103 )
POO, V6«. ACq HGA, MCC-H UPLINK (LM VECTOR AND CSM VECTOAl
PZO (4*)(0,23E/0e,O)
P32 (K>1)
Vi3. VSr, V67 +JT
SET/VHF (5J, TEMilNATE SAT. V93, VNF (5), V90
(MARK TO CSI -12)
jiF’viiFlv93r'viiF'oiiLY""l
V90<CSK AND LH)
P32 FINAL COKP, COPT IH CSI PAD
P40 (73’)IO.)q3/20B.0), V56, SPS SETUP, «DC ALIGN
IlH CSI(I65 <10 27)<49 G.O.O) I. PT6
CSH CSI 1-50 5.0.0)10.1SO/258,0)
P20 (43*)(0. 230/301,0) ,
»57, V87, 3 SAT NARKS, VG7 (*02000, *00020, tOOOOl)
(HARK TO PLANE CHANCE -I]
V90 LH TOOT, COPT LH PC PAP
IlN plane CHANGEdOb 09 iqMO.230/220,0) I P76
B33
V57. T87, 3 SXT HARKS, V93 , VS7 (HARK TO COH -15)
-151-
7.T5, P Dig + 19:22 Preferred Lift-off (Tg) (CSM Active)
7.15.1 Summary
This rescue results from an abort approximately 19
•minutes and 22 seconds into powered descent- .where the
descent was initiated at the second opportunity. This
coincides with the first preferred lift-off (Tg) after
PDIg. The LM is assumed to have reached a fixed 10 X 30
orbit. The rescue phasing burn occurs af a fixed GET
defined as 50 minutes from that insertion cut-off time
associated with an abort at PDIg -f- 14.5 minutes. CSI-j
occurs one-ha-lf rev after the rescue phasing burn, with
CSIg occurring one-half rev later. CDH occurs one-half
rev after CSIg.
7.15.2 PDI^+ 19:22 PREFERRED UFT-OFF (T^) (CSM ACTIVE)
52-
-154-
8,0 REFERENCES
8.1 Mission Requirements SA-506/CSM-1 07/LM-5 , "G" Typs
Missfon, Lunaw Lsn<ii'ng; dated 5 'March 1969.
8.2 Spacecraft Operational Trajectory, Volume 1; Operational
Mission Profile Launched 16 July 1969; MSC Internal
Note No. 69-FM-98; dated 16 May 1969.
8.3 Shreffler, J. H.; Onboard Tracking Schedules for
Mission F and G; Memo No. 69-FM46-29,- -dated 7 February 1969.
8.4 Shreffler, J. H.; On the Efficacious Utilization of
VHF Range Data when Sextant Marking is Interrupted;
Memo No. 68-FM46-482; dated 19 December 1968.
8.-5 Pixley, P. T.; F Rendezvous Navigation Mission
Techniques Panel Meeting; MSC Memorandum 69-FM46-107;
dated 10 April 1969,
Guidance System Operations Plan for Manned CM Earth
Orbital and Lunar Missions Using Program COLOSSUS 2
(COMANCHE REV. 44 ,45 )Section 4 Operational
Modes, Revision 7; dated March 1969.
8.7 Guidance Navigation and Control Command Module
Functional Description and Operations Using Flight
Program COLOSSUS 2A (COMANCHE 55) Volume II,
Normal Procedures; dated June 1969.
-155-
6.8 Apollo Operations Handbook Command and Service
Modules - Volume II, Operational Procedures;
dated 17 April 1969.
6.9 Diekelman, D.P.; MDAC Apollo Design Note No. 114,
"Evaluation of the Current Navigation Schedule for Mission
G Lunar Rendezvous;" dated 4 June 1969.
6.10 Worley, N.; MDAC Apollo Design Note No. Ill,
"Mission G Nominal Reference Trajectory;" dated
7 May 1969.
8.11 Preliminary Apollo 11 Flight Plan; AS-506/CSM-107/LM-5;
dated 15 April 1969.
8.12 Puschinsky, R. W.; McRae, M.; Otto, R,; CSM Rendezvous
Procedures D Mission, Final Revision A; dated
1 February 1969.
8.13 Tindall, H. W. ; Apollo Mission Techniques Mission F
and G Lunar Orbit Activities - Volume I, Techniques
Descriptions, MSC Internal Note No. S-PA-9T-044,
dated 28 February 1969.
8.14 Lunar Contingency Rendezvous Group; "Preliminary
Operational LM Abort and Rescue Plan for Apollo 11
(Lunar Landing Mission);" dated 6 June 1969.
-156-
8.15 Arceneaux, W.K.; MDAC Apollo Design Note No. 117,
"Evaluation of the Nominal Mission G Lunar
Rendezvous Navigation Mark Types and the A Priori
Measurement Range Variance (VARMIN);" dated
12 June 1969.
8.16 Fudurich, R.; MDAC Apollo Design Note No, 107,
"Effects of a LM Tracker Light Failure Upon a
CSM Active Rendezvous During Mission F;" dated
21 April 1969.
8.17 Carrico, L. D.; Paddock, S. G.; MDAC Apollo Design
Note No. 113, "The Effects of VHF Only Navigation
on the Terminal Rendezvous Phase of Mission F;"
dated 16 May 1969.
8.18 Revision 1 to Spacecraft Operational Trajectory
for Mission G, Volume 1; Operational Mission
Profile Launched 16 July 1969.
8.19 Diekelman, D., MDAC Apollo Design Note No. 114,
"Evaluation of the Nominal Mission G Lunar Rendezvous
Navigation W-Matrix Diagonal Elements and Initialization
Schedule."
8.20 Mangiaracina, C., Diekelman, D,, MDAC Apollo Design
Note No. 118, "Evaluation of the Current Mission G
CSM Nominal Lunar Rendezvous Navigation W-Matrix
Diagonal Elements and Initialization Schedule."
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